WO2023080795A1

WO2023080795A1 - Apparatus and method for reducing particle current and use of the effect

Info

Publication number: WO2023080795A1
Application number: PCT/NO2022/050249
Authority: WO
Inventors: Roy Eriksson
Original assignee: Roy Eriksson
Priority date: 2021-11-07
Filing date: 2022-11-07
Publication date: 2023-05-11
Also published as: WO2023080795A4; NO20211340A1

Abstract

A sun barrier creating apparatus and weather modification system for spreading substances from an orbit around the Sun and reduce at least one type of particles from the Sun and reduce the risk of damage and natural disasters. The spreading is made by automatic flying spacecrafts controlled from a control center located on Earth. The apparatus includes a spacecraft and a controller coupled to the spacecraft. The apparatus further includes a spreading device configured to spread substances and or laser beams. The system comprises a radar sensor configured to scan the sun barrier material and to provide a sensor feedback signal to the controller with respect to an intrinsic characteristic of the sun barrier material. The controller is configured to instruct spreading of substances or laser beams based on stored instructions and the feedback signal to create the desired temperature and more predictable weather and weather forecasts on Earth.

Description

Title Of The Invention:

Apparatus and method for reducing particle current and use of the effect.

TECHNICAL FIELD

The present invention relates to reducing the risk of especially heat related damage and disasters by placing a Sun barrier in orbit around the Sun to regulate the passing particles in the direction of a specific object or area, such as photons from the Sun on its way to Earth, and where the effect is regulated by changing the area and or density of the Sun barrier and whish is continuously monitored by a Control Center. And where the effect of shading affects the weather and used to calculate weather forecasts and predict the degree of louvered risk for natural disasters.

BACKGROUND OF THE INVENTION

Radiation and other particles from the Sun and other sources in the universe can sometimes cause damage to living organisms and electronic components. For example, the Earth's average temperature increases, and heat is considered to create many negative effects, such as warmer and nutrient -poorer seas and increased sea level that are at risk of flooding large areas. The Earth's decreasing snow and ice cover is also considered to contribute to higher temperatures by reducing the reflection of solar radiation. In addition, large amounts of gas hydrates are found in Earth’s coldest places such as the Arctic and Antarctica and are volatile gases, such as methane, which are encapsulated in the crystal structure of the ice. Furthermore, forest fires are a major and increasing problem in hot weather and drought, and huge areas and large amounts are lost annually, and the fires contribute to atmospheric pollution. The increase in temperature is also thought to change ocean currents, kill coral reefs, and increase ice melting. The weather is also considered to be more extreme with significantly more and more powerful vortex storms, as well as more downpours and long periods of drought. The damage from warming is expected to amount to trillions of dollars annually as early as 2050, and several researchers are even more pessimistic. The reason for the increase in temperature is partly disputed, with many scientists believing that the main cause is carbon dioxide, methane and other air pollutants that is spread in the atmosphere and increase the Sun’s warming effect.

The Sun is considered, since its formation, to have continuously increased its energy release and has produced large readings on Earth's temperature, and the continued increase in temperature is expected to make the Earth uninhabitable in the future. There are still many unanswered questions about the effects of the Sun's varying energy release from different places on the surface. And there is no doubt that the gravity of planets orbiting the Sun affects its liquid surface and thus the reactions that emit energy to the environment. For example, the Sun directs different parts of the surface directly towards the Earth at different times and emits a variety of radiation and other particles, and photons will of course hit the Earth from all the Earth's visible part of the Sun's surface. And if the sun increases its energy release to Earth, then even a clean atmosphere may not be enough to lower the temperature to the desired level. It is often difficult to predict the future location of solar storms on the surface and the impact of the Sun's magnetic field on the ejected particles, and in which direction the particles will essentially travel. And because the Sun is enormous, and the round shape means that it is a relatively smaller part of the Sun's surface that points straight to Earth. In addition, this point changes continuously because the Sun rotates around its own axis of rotation and during the Earth's orbit around the Sun. Particularly difficult to calculate are the effects of the Sun having a variable rotational speed due to the Sun missing a solid surface, where it takes 25.05 days to do one turn at the equator and 34.4 days at the poles. And that there is also a large rotational flow of solar wind that increase the speed to sometimes reach almost the speed of light in the Sun’s atmosphere, and some research have shown that this happens when there are switchbacks in the magnetic fields that force the electrons back towards the Sun. Earth's orbit around the Sun is to varying degrees elliptical and the distance varies throughout the year and the smallest distance, 147,100,000 kilometers, occurs in January and is at most 152,100,000 kilometers in July. This also means that the energy that hits the Earth varies by about 3.5% from the average. Today's seasons on Earth are largely due to the Earth's axis tilting about 23.4 degrees in its orbit around the Sun. The effect of the Earth being effectively shaded from a distance can be experienced during a solar eclipse that occurs when the Moon passes between the Earth and the Sun. The Moon's diameter is 3474 kilometers and since the Sun's diameter is about 400 times larger than the Moon and is 400 times further away, the celestial bodies seem the same size as seen from Earth. However, the Moon can never shade the entire illuminated side of the Earth at the same time because the Earth is significantly larger with a diameter of 12,742 kilometers, and depending on the location, this would require an obstacle with the area corresponding to the Earth when positioned near the Earth to an area corresponding to the Sun when positioned near the Sun. Earth's average distance to the Moon is 384,400 kilometers and to the Sun it is on average about 150 million kilometers, and the diameter of the Sun is 1.39 million kilometers, which is 109 times larger than Earth's. The light that leaves the Sun's horizon reaches the Earth's horizon after about 8 minutes and 19 seconds, but the distance varies and when it is at its shortest it takes about two seconds less time. The time it takes from the Sun's surface down to the Earth's surface is usually rounded off to 8 1/2 minutes, and for the so-called solar wind it usually takes between 2 to 4 days to reach Earth, and new research shows that the solar wind can sometimes be ejected at close to the speed of light. When comets come close to the Sun, ice and other matter can be heated and emitted and can often be seen as two tails, where the tail of dust and uncharged particles follow the comet in a slightly curved orbit, while the ion tail consisting of gas is always directed away from the Sun as it is more affected by the solar wind and magnetic field. Ion tails longer than 1 AU have also been recorded, which corresponds to the distance between the Sun and Earth.

Radiation and particles from space and especially from the Sun can cause many different types of problems. But particles also come from explosions in the universe, such as supernovae and nebulae. The particles can damage, for example, electronics in satellites and electronics on Earth, and especially vulnerable are the thousands of satellites that are to be included in the Earth -wide internet. And, of course, there is a particular risk to people who are outside the Earth's protective atmosphere and magnetic field. For Earth, scientists also expect that the magnetic field between the north and south poles will be reversed in the same way as it has done several times before, and we are now considered to be in the period that this can statistically happen again. The magnetic field will then probably not be able to protect the Earth from particles from space for the time it takes for the magnetic field to stabilize again. This means that protection against unwanted particles must be ready when this happens. I also believe that almost all people want proven protection against a worst-case scenario and which can be used quickly.

There is therefore a need for a solution that reduces the above problems.

PRIOR ART

It is, of course, known that clouds have a cooling effect on everything that is shaded and that the effect increases when less Sunlight is released through the cloud. It is also known that large volcanic eruptions have lowered the average temperature across the globe by spreading particles into the atmosphere. It is also known to cooling areas in different ways, for example, different chemicals or smoke have been proposed in the upper atmosphere. In, for example US Patent 9363954B2 Atmospheric delivery system for spreading particles in the stratosphere and creating clouds, as well as US Patent 5003186A Stratospheric Welsbach seeding for reduction of global warming. And US Patent 3222675A describes means for positioning a plurality of elements in orbit abut a celestial body. Researchers have discussed several different solutions for the spreading of various substances in the atmosphere, such as spreading substances that scatter light, such as lime or sulfur dioxide from helium balloons at an altitude of 25 kilometers. Another proposal aims to stimulate and encourage marine clouds to reflect more Sunlight back into space. There are also suggestions for large umbrellas or curtains placed between the Earth and the Sun, but some of the problems with physical obstacles are that it takes a huge number for the effect to be measurable. And that each obstacle must be equipped with rocket engines so as not to be driven away by, for example, the solar wind, and will also be hit by gravel and the like from passing comets and asteroids. And if it is not placed in its own orbit with direction and speed adapted to the Earth so will the obstacle soon end up in a location it does not give the desired effect. Although described methods such as smoke and chemicals near a planet work, it is difficult to avoid areas that are not desired to be shielded may suffer from reduced energy supply, while the spread of particles that may end up in the atmosphere would mean that the particles become floating in the air for a period. And with the risk of unwanted consequences in the atmosphere or when the particles land on land or in the ocean. Also, the Earth rotation, winds and air currents can accumulate the substances that are spread, and it will be difficult to see the effect and almost impossible to calculate where everything ends up. In addition, the rotation of the Earth and strong jet streams make it very difficult to shield only the chosen area with chemicals and the like, and in addition, it is common for the wind to blow in different directions at different altitudes. And when different weather systems collide, it becomes extra difficult to predict where scattered particles end up. In addition, the Earth rotation means that the angle of the Sun is constantly changing with each point on Earth, and a particle barrier in or near the Earth's atmosphere cannot therefore be given a fixed location above a specific point on Earth. Continuous shadowing of the same point on Earth requires the obstacle to re-wreath the entire Earth or to follow the movement of the Sun, which is very difficult due to said varying wind directions and wind speeds. And existing technology does not allow us to protect other planets or high-lying satellites orbiting the Earth or, for example, during transport to the Moon or Mars, or to protect personnel or equipment located on said planets. In addition, it may be desirable to be able to quickly interrupt the cooling effect, if necessary, which can be difficult with particles present in the Earth's stratosphere or atmosphere.

Furthermore, there can be great resistance to the spread of substances in the vicinity of the Earth, which is why this will be almost politically impossible to implement. And it can be expected that many will require that particles cannot fall on Earth and that a cooling effect can be constantly monitored and controlled, and if necessary, changed so that the effect can be reversed completely without the residual cooling effect on Earth.

Furthermore, there are several methods to try to reduce the effect of the energy from the Sun, for example, in the Norwegian patent number 337419, a cooling machine is working according to the principle of a freezer box, but where one of the sides of the box is the surface, and where the coolant is, for example, liquid nitrogen, -196 °C, helium, -272 °C or dry ice -78 °C where the chiller is a closed unit with, for example, the ground, water or snow during the continuous movement forward. Cooling in the closed cooling machine is of course effective in limited areas, such as wet ski tracks or ice roads or creating ice floes on the high seas but cannot cool larger areas.

As is well known, there are also a variety of laser systems or Light Amplification by Stimulated Emission of Radiation, intended for many different civilian and military purposes. The primary wavelengths of laser radiation for current military and commercial applications include the ultraviolet, visible, and infrared regions of the spectrum. Examples of lasers include Solid-State Lasers, Chemical Lasers, Gas Lasers, Free electron lasers and Fiber lasers as well as a type commonly referred to as Solar-pumped lasers, all of which are also available in a variety of designs. One problem is that lasers used in atmospheres get short range due to atmospheric thermal blooming, which electro -lasers try to solve by ionizing its target path, and then sends an electric current down the conducting track of ionized plasma. And plasma acceleration is used for accelerating charged particles such as electrons, positrons and ions, and there are successful attempts to shoot laser beam through various substances and compositions to manipulate and induce a different effect on the beam. Lasers are usually divided into continuous lasers, which emit a constant beam of light, and pulsed lasers, where a controlled pulse of light is emitted and which can be very short and have very high power, up to 10_l 8 W exawatt. Maser is based on the same technology as lasers but uses microwaves. The laser beam can be made narrow or wide and manipulated in many ways as for example tophat beam and specialized optical systems can produce more complex beam geometries, such as bessel beams and optical vortexes. Depending on the application, various substances to amplify light coherently are used for example helium-neon, hydrogen fluoride, deuterium fluoride, yttrium aluminum yam. Powerful lasers can also be very power-intensive, while modern pulsed lasers for military moving craft can emit laser beams at a current cost of just a few dollars each. To produce power, there are today so-called mobile nuclear reactors that are mainly used in military applications, for example in submarines and aircraft carriers. For applications used in space, solar cells are commonly used to charge batteries for the operation of electrical components. Acceleration of particles to near the speed of light can also be created using magnets, where the particle accelerator in Cern is a known example, but magnets are also used to stabilize particle current from lasers. And several research teams are also trying to develop lasers that can replace today's particle accelerators. It has also been suggested that satellites can be accelerated using lasers firing at the satellite, and the method has also been proposed to cause large comets or asteroids heading for Earth to change direction. Photons can be destroyed and transformed in different ways, and here we can mention Compton scattering, and is the scattering of a photon by a charged particle, usually an electron, and the photoelectric effect, and is the emission of electrons when electromagnetic radiation, such as light, hits a material. Where experiments carried out to test the photoelectric effect show that photons directed at metal sheet can be completely destroyed by electrons from the plate, which also indicates that the corresponding effect can be obtained if said electrons are directed at colliding photons. A preferred position to locate satellites today are on the Lagrange points where gravitational attraction of, for example, the Sun and that of Earth combine to produce an equilibrium. If placed at Lagrange point LI and the object is directly between the Sun and Earth, then Earth’s gravity counteracts some of the Suns pull on the object, and therefor increases the orbital period of the object. The closer to the Earth the object is, the greater this effect is and at the LI point, the orbital period of the object becomes exactly equal to Earths orbital period. The L4 and L5 points are even more stable and lie at the third corners of the two equilateral triangles in the plane of orbit whose common base is the line between the centers of the two masses, such that the point lies behind L5 or ahead of L4 of the smaller mass with regarding to its orbit around the larger mass. The mathematical formulas used today for placing satellites in one of the orbits LI, L4 and L5 are used in each launch to these locations and is therefore not reproduced here.

Furthermore, of course, the manufacture and launch of today's space shuttles and other spacecraft and all the necessary equipment and computer programs for them to complete their various missions in space are known technologies. Furthermore, wireless control and other communication with, for example, satellites are well proven technology, and on the planet Mars, robots have been landing and carrying out research missions for years. And even docking between satellites, for example, can now take place automatically or be controlled from a Control Center on Earth. Furthermore, the technology and necessary equipment to place objects in orbits in space with different types of space shuttles are of course known technology, as well as to communicate and, if necessary, remotely control different organs on the space shuttle and the object placed in orbit, such as GPS satellite. Furthermore, the exact position in the orbit of any current time can be calculated for different planets and other objects that are in a fixed orbit around the Sun, for example, it can be calculated which part of the Earth is directed towards the Sun at a time several years in the future. Of course, it can also be calculated the position, direction of movement and speed of objects with their own orbit around the Sun for the object to be between the Sun and Earth for as long as possible, and the technology is currently used for research satellites, for example, to research the Sun located at Lagrange point LI. It is also known that by means of radar, laser, and other acoustic and photographic systems map any matter regarding, for example, spreading and density and to determine the exact location in a coordinate system with GPS. Here can be mentioned radar systems for identifying different types of clouds and that collected data is then used to calculate weather forecasts, as well as to scan and determine for example buildings, geological formations in and above ground, and to identify terrain etc., and that the collected data can be used to make a map. And the Meteosat Third Generation (MTG), will use six weather satellites where four of them will take pictures in visible and infrared light of weather systems and clouds. These satellites will also be able to see lightning in real time and aerosols in the atmosphere. Two of the MTG satellites will have infrared instruments that measure temperature in several layers of the atmosphere. And researchers use spectrum analysis to determine constituents of asteroids. But I believe it is new to reduce the risk of natural disasters and other damage by particles from the Sun in the way and location described here by dispersing/spreading substances in weightlessness from an inner orbit around the Sun and by giving the obstacle a speed to prolong the effect. And in at least one embodiment use the gravitational forces between the Sun and that to be protected in order to prolong the effect, as well as scan and position created clouds, which does not exist today, and make a map that can be used to calculate the effect and if more substances need to be spread in a specific location. And calculate weather forecasts etc. of the manufactured clouds determined and estimated future obscuring effect, and how this affects the local weather in one or more places determined by, for example, said MTG systems.

DESCRIPTION OF THE INVENTION

It is an object of the invention to provide a method and a means for protecting an object or area from unwanted particles or unwanted amount of particles from the Sun, by automatic spreading of substances in an inner orbit around the Sun, in order to create a Sun barrier and reduce the number of particles from the Sun in the direction of a selected object or area traveling in an outer orbit. And reduce or eliminate undesirable effects, such as lowering the temperature or reducing the risk of damage to electronics, by causing particles from the Sun to collide with substances in the Sun barrier.

Where a Control Center placed on Earth is the coordinator in a weather modification system comprising a computer unit including a controller and a communication unit coupled to the computer unit. And where at least one remotely monitored and from said Control Center controllable apparatus, here also called spacecraft, and which is equipped with spreading devices, for example comprising a nozzle, for spreading the means, here also called substances and laser beams to constitute said Sun barrier and stopping the passage of said unwanted particles or unwanted amount of particles such as photons or particles from eruptions on the Sun. The Sun barrier is placed in its own orbit around the Sun in the vacuum of the universe, between the Sun and the object or area to be protected, for example Earth or other spacecraft on its way to or from, for example, the Moon or March. Where the Sun barrier that is to stop unwanted particles is given a foresight, speed, direction, size, density, and location that corresponds to the location particles from the Sun is determined to pass on their way to the protected object or area, at estimated time or time interval. And by adjusting the speed and direction of movement in said orbit of the Sun barrier, to the coordinates, speed, and direction of movement to what is to be protected, for example, satellites on their way to the Moon or Mars, they can be protected even when they are not in a fixed orbit around the Sun.

It is another object in at least one embodiment of the invention that the Control Center Control an apparatus that includes an automatic flying spacecraft and a controller coupled to the spacecraft. The apparatus further includes a spreading device coupled to the spacecraft; the spreading device configured to spread substances into a path in orbit around the Sun. And is further configured to provide a sensor feedback signal to a controller. The controller is configured to instruct placement of at least one kind/type of substance into the orbit based on in a storage device stored information of said feedback signal, and incoming new orders from said Control Center located on Earth.

It is another object in at least one embodiment of the invention that at least one censor includes at least one camera for determining of, for example, the Sun barrier shape, size, content, speed and direction of movement, and geographical location in space. And advantageously by several cameras that take pictures in different wavelengths. By comparing a series of images, it can also be calculated how the cloud develops as well as speed and direction of movement. The information is routed to the Control Center in the same way as for all other censors, for example, temperature or particle current, and the censors can be placed on Earth or on satellites in space.

It is another object in at least one embodiment of the invention that it is comprising a Sun barrier detection apparatus and include a housing coupled to a spacecraft. The apparatus further includes a controller coupled to the housing. The apparatus includes a radar sensor coupled to the housing. The radar sensor is configured to scan a path with spread substances in the Sun barrier to at least a depth greater than the depth at which photons can pass the Sun barrier material, wherein the radar sensor is further configured to provide a sensor feedback signal to the controller with respect to an intrinsic characteristic of the Sun barrier material. The apparatus further includes a location sensor coupled to the housing. The location sensor is configured to provide a location feedback signal to the controller. The controller is configured to create a map of the Sun barrier material based on the sensor feedback signal and the location feedback signal. The method further includes, in response to the intrinsic Sun barrier characteristics, instructing a spreading mechanism coupled to the spacecraft to spread substances and/or laser beams from or in a path orbiting the Sun.

It is another object in at least one embodiment of the invention that it relates to a method of mapping Sun barrier characteristics with a spacecraft having a controller. The method includes receiving operating parameters through a user input of the spacecraft. The method further includes navigating the spacecraft through a path around the Sun. The method further includes detecting intrinsic Sun barrier characteristics of a Sun barrier material through a radar unit coupled to the spacecraft, wherein the radar unit is configured to scan the Sun barrier material, here also called substances, up to a designated depth beneath a surface of the Sun barrier, and wherein the radar unit is further configured to provide a sensor feedback signal to a controller of the spacecraft. The method includes tracking a location of the spacecraft through a location sensor coupled to the spacecraft. The method further includes creating a map of an area of space traversed by the spacecraft, wherein the map includes detected intrinsic Sun barrier characteristics, wherein the map is configured to be later updated to include the location of new spread substances. It is another object in at least one embodiment of the invention that it relates to a sun barrier creating apparatus comprising: An automatic flying spacecraft capable to fly to an orbit around the Sun; A controller coupled to the spacecraft; A spreading device coupled to the spacecraft, the spreading device configured to spread substances or laser beams from an orbital path around the Sun and create said sun barrier; And that the sun barrier are configured to protect an object or area with a determined location and traveling in an outer orbital path around the Sun; A location sensor coupled to the spacecraft, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine the direction of travel, speed, and location of the spacecraft; and. A time unit coupled to the controller; Wherein the controller is configured to: Determine a designated spreading location based on the sensor feedback signal and stored information for at least one location from which said substances can be spread at a specific time or period; And, means for moving the spacecraft to a spreading location in said orbit around the sun; And, means for changing speed and direction of travel to stored information; And, means for instructing spreading of substances or laser beams and create a sun barrier at the designated spreading location at a specific time or period.

It is another object in at least one embodiment of the invention that it relates to a sun barrier penetrating radar sensor placed on Earth or coupled to a spacecraft, the radar sensor configured to scan the Sun barrier material to at least a designated depth beneath a surface of the sun barrier, wherein the radar sensor is further configured to provide a sensor feedback signal to a controller with respect to an intrinsic characteristic of the Sun barrier material; And, a location sensor coupled to the radar sensor, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine a specific location of the radar sensor unit and of extrinsic sun barrier characteristic, based on the specific location scanned by the radar sensor and the distance and angle to the different parts of the sun barrier; And, that the controller is further configured to create a map of the Sun barrier material based on the sensor feedback signal and the location feedback signal; And, that the map provides information that can be used to determine the effect of the Sun barrier and to calculate future requirements for the spreading of substances; And, that the determined obscuring/shading effect and determined future spreading of substances that affecting said effect are used to determine a percentage reduction in the radiation of particles from the Sun over a specified period of time; And, that the calculated reduction in solar radiation of at least one type of particle is used to calculate weather forecasts, for example, by calculating the impact on temperature in air, water and soil.

It is another object in at least one embodiment of the invention that it relates to a sun barrier creating apparatus and that a sensor feedback signals from the radar sensor and the location sensor are further provided to a control center comprising a communication unit coupled to a computer unit including a storage unit and a controller; And, that the storage unit configured to include a value for limits of the shading effect and a value for the preferred shading effect to be achieved, i.e., reduction in temperature and or reduction in particle current from the sun; And at least one temperature sensor placed on the protected object or area configured to provide a temperature feedback signal to the controller, wherein the controller analyzes the temperature feedback signal and correlates the temperature value to in the storage unit stored value for preferred value and limit value; And, at least one particle current sensor configured to provide a feedback signal to the controller wherein the controller analyzes the feedback signal to determine a specific value of at least one type of particles in the particle current and correlates the value to in the storage unit stored preferred value and limit value; And, that the controller determines if the present spread of substances needs to be changed, i.e., increased, reduced, or maintained; And, that the substances for creating a sun barrier comprises at least one of the following: An organic substance; An inorganic substance.

It is another object in at least one embodiment of the invention that it relates to at least one spacecraft orbiting the Sun carrying substances for stopping dangerous particles from erupting in the Sun. And configured to only spread substances after identified said dangerous particles is determined to travel in a direction where they will hit the protected object or area, for example the Earth, the Moon or Mars or other spacecrafts. The spreading device can, for example, be activated by a Control Center that monitors the Sun 's thermal activity. The controller will then regulate the speed on the spacecraft so that the substances can be spread where the dangerous particles will pass the spacecrafts orbital path.

It is another object in at least one embodiment of the invention that it relates to a method for creating a sun barrier orbiting the Sun and protecting an object or area from at least one type of particles from the Sun and comprising the following steps: Determine location for an object or area to be protected in a location system, for example a coordinate system including the Sun; And coupling a controller to a spacecraft capable of automatic flying to an orbit around the Sun; Coupling a spreading device to the spacecraft, the spreading device configured to spread at least one type of substance or laser beams from an orbital path around the Sun and create said sun barrier; Coupling a location sensor to the spacecraft, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine the direction of travel, speed, and location of the spacecraft; And, coupling a time unit to the controller, wherein the controller is configured to: Determine a designated spreading location based on the sensor feedback signal and in a storage unit stored information for at least one location from which said substances can be spread at a specific time or period; And, navigating the spacecraft to the determined spreading location in said orbit around the sun; And, instruct spreading of said substances or laser beams and create a sun barrier at the designated spreading location at said specific time or period.

It is another object in at least one embodiment of the invention that it relates to a method for a weather modification system supervised and controlled from a control Center: The system comprises; evaluation means comprising a computer unit including a communication unit coupled to a storage unit and a controller placed in the control center; Communication and data transfer between said control center and at least one automatic flying spacecraft whose controllable means can be monitored, oversteered, and remotely controlled from said control center; And, collecting quantities or a value from a plural of sensors measuring temperature and or particle current from the Sun; And, collecting quantities or a value from radar sensor unit for measured size and density on the sun barrier; And, determining the shade effect at any given time by analyzing the collected data from temperature sensors and radar sensor; Compare the stored desired shade effect with the actual measured shade effect and, in case of deviation, calculate ho w much substances need to be spread to achieve the said desired values; And, sending control signals to one or more spacecraft to change the amount of spread substances to the new value; And, use of the actual calculated shade effect and the effect of the planned spread of substances to calculate the total shade effect over a period of time; and,

It is another object in at least one embodiment of the invention that by substances is meant here everything that can stop any of the different types of particles from the Sun and can be spread or dragged by a spacecraft from an orbit, for example water, smoke, ash, dust particles, carbon, gases, chemicals, blankets, and or laser beams. It is another object in at least one embodiment of the invention that at least one of the Sun barriers is a cloud of at least one type of substance and that the number of particles is largest in the center of the Sun barrier and gradually thins towards the periphery. It is another object in at least one embodiment of the invention that at least a part of at least one Sun barrier has the form of a line. It is another object in at least one embodiment of the invention to produce, storage, and transport the substances, from the factory it is manufactured and at least part of the way to the location it is to be spread in an orbit around the Sun. It is another object in at least one embodiment of the invention that the substances are manufactured in space, or a by-product of manufacture of other products, gods or chemicals intended for transport to Earth, the Moon or Mars. The spacecraft is then equipped with, for example, robots and computer programs to automatically handle the production and distribution of finished products, etc. and where the waste can be used for the production of a Sun barrier.

It is another object in at least one embodiment of the invention to describe method for creating a sun barrier orbiting the Sun and protecting an object or area from at least one type of particles from the Sun, comprising: Placing a control center on earth, the control center capable of communication, supervision and controlling at least one automatic flying spacecraft capable of flying to said orbit by a controller coupled to the spacecraft; And, determine the location, direction of travel, speed, and distance from the Sun for said object or area; And, decide location and direction of travel for the orbital path for the sun barrier; and, calculate the travel path for said particle from the sun to be stopped; And, analyze and determine a spreading location where and when the particle from the sun to be stopped will pass the decided orbital path for the sun barrier; And, transporting at least one type of substance in a container with an automatic flying spacecraft to the determined spreading location; And, spreading the substance from the container via at least one nozzle and create a sun barrier orbiting the Sun at determined location, time, and speed.

It is another object in at least one embodiment of the invention that it relates to the Use of a Sun barrier to create a shading effect on an object or area and reduce the risk of damage and natural disasters in accordance with any of described apparatus and methods, and where the sun barrier reduces the temperature in matter, soil, air, water and organic life on the protected object or area; And, that the reduced temperature reduces the risk of damage caused of at least one of the following heat -related disasters: forest fires, rising sea levels, vortex storms, desertification, ice melting, changing ocean currents, oxygen level in water, heatstroke on living organisms, torrential rains, flooding of rivers, damage to electronics; And, wherein a specific reduction in temperature is determined to result in a calculated lover risk of at least one of said damage or disaster and is agreed and insured.

It is another object in at least one embodiment of the invention that at least one of the substances, which are to be used to create a Sun barrier, have at least one color, for example black, gray, or white. It is another object in at least one embodiment of the invention that at least one of the substances, which are to be used to create a Sun barrier, is colorless. It is another object in at least one embodiment of the invention that the substances, which are to be used to create a Sun barrier, comprises ashes from deceased and cremated person or animals and is spread in space against payment, where the object is to partly cover the cost of shipping and where the person or pet is beneficial even after death.

It is another object in at least one embodiment of the invention that certain cooling effect for a specified time or period is used to calculate weather forecasts for a specific object or area. The information is used in conjunction with regular weather forecasts, and it is calculated what effect the cooling will have on the future weather. Here, for example, lower temperatures can be mentioned, where, for example, rain can instead fall as snow. To make the calculations of the effect so can for example the percentage reduction of the solar radiation during said specific time or time period be used. Today's weather forecasts are based on known irradiation from the sun to different areas of the Earth during different seasons and angles to the sun for these areas and, for example, how different air layers, soil and water are affected by this known solar radiation and how winds and weather systems are affected and spread with Earth rotation. This invention aims to provide a new adjustable lower value for solar radiation, which can of course be given a value with very huge effect on the weather that is formed all over the world. Continuous monitoring is therefore important and that a coordinator is directly linked to the different sensors monitoring the effect, and the spacecrafts that spreading substances into space, in order to make the necessary adjustments to the amount of spreading and or spreading locations. And is here called a weather modification system and comprising said Control Center located on Earth.

It is another object in at least one embodiment of the invention that the apparatus and method to spread substance in the desired direction by tuming/pointing one or more nozzles, or opening one or more gaps or equivalent, in the desired direction. And or turn the spacecraft with jet engines so that said nozzles or gaps are directed in the direction the user wants to spread substances. It is another object in at least one embodiment of the invention to manufacture the spacecraft, which is to spread said substances, and to manufacture the cargo ships which are to transport the substances for creating said Sun barrier, as well as all transport of the vessels. It is another object in at least one embodiment of the invention to manufacture and transport the rocket fuel and other supplies to the cargo ships, as well as to the spacecraft. It is another object of the invention to manufacture and use of computer programs, radio transmitters / receivers, censors, and other equipment necessary for communicating and monitoring said cargo ships and the spacecraft from at least one Control Center located on Earth. It is another object in at least one embodiment of the invention that at least parts of a spacecraft, cargo ships and other satellites are painted in a non- reflective black color to avoid reflection of sunlight against populated planets or manned spacecrafts. It is another object in at least one embodiment of the invention that a coordinate system comprising our solar system are used to position-determine the object or area to be protected and the location of the Sun barrier and the spacecraft, where the Sun is given a fixed point with distribution in the coordinate system. But where the Sun can rotate around its own axis without affecting the coordinate system. Then put a fix point in, for example, a distant star. There then planets and satellites move between different coordinates in this fixed coordinate system around the Sun. And where places on Earth, Moon and Mars can be determined by GPS or equivalent local coordinate systems. It is another object in at least one embodiment of the invention that the spacecraft and the Sun barrier can be used to reduce damage of particles from the Sun when the Earth's magnetic field shifts poles, as they have done several times before at even intervals, and where the time is now considered to be in for a new one. It is another object in at least one embodiment of the invention to manufacture and install computers and computer programs in said spacecraft and cargo ship and intended to control and regulate the moveable organs of the device and to communicate with the Control Center located on Earth with the communication device. It is another object in at least one embodiment of the invention to manufacturing and transport of rocket fuel for said spacecraft and intended for the operation of the device's jet engines. It is another object in at least one embodiment of the invention to transport consumables and supplies to the spacecraft during its orbit around the Sun by cargo ships carrying cargo from, for example, the Earth, the Moon or another planet or comets etc.

I It is another object in at least one embodiment of the invention to also reduce the shearing effect of the solar wind on the outer atmosphere, thereby preventing the thickness of the atmosphere from decreasing around selected objects, for example around the Earth or in the future, the created atmosphere on, for example, Mars or the Moon. It is another object in at least one embodiment of the invention to reduce the risk of different types of extreme weather, such as strong whirlwinds, and by shadowing the Sun and thereby reducing the energy supply to air, airborne water, and surface water, while reducing the risk that whirlwinds can grow large on warm surface water in the oceans. It is another object in at least one embodiment of the invention to reduce the risk of forest fires starting and to facilitate extinguishing by reducing the temperature of plants, soil, and air. It is another object in at least one embodiment of the invention to enable the desired temperatures to be obtained at the desired seasons in different geographical areas, thereby, for example, enabling today's local flora and fauna to survive, while reducing the risk of the area being taken over by unwanted species. It is another object in at least one embodiment of the invention to reduce the annual ice melting of ice in glaciers and at the poles, as well as, if necessary, enabling increased icing, which lowers sea level and increases the chances of survival for species that require chilly climates. It is another object in at least one embodiment of the invention to reduce the risk of skin cancer as well as heat-related conditions such as heatstroke, as well as reduce the problems with radiation during, for example, air travel at high altitudes and stay in a thin or no protective atmosphere.

It is another object in at least one embodiment of the invention to reduce the risk of living organisms being harmed by the rising sea temperature, as well as the change in various substances in the water that an increasing temperature can lead to, where, for example, corals are considered sensitive to changes in ph. value and oxygen level. It is another object in at least one embodiment of the invention to cool seawater to desired temperatures in selected places so that, for example, the gulf stream does not change its course. It is another object in at least one embodiment of the invention to create a better and safer environment for people and wildlife in places that today are often affected by extreme weather, such as whirlwinds, droughts, torrential rains, or forest fires. It is another object in at least one embodiment of the invention to reduce the risk of natural disasters and thus high insurance premiums and other indirect costs, for example for buildings, boats, vehicles, or forests. It is another object in at least one embodiment of the invention to enable the regulation of certain types of particles from the Sun, such as particles of a certain wavelength or particles of a certain speed with a specified direction of travel. It is another object in at least one embodiment of the invention to reduce natural emissions of methane from particularly thawing thaw on the tundra as well as various greenhouse gases considered to be emitted from the world's oceans at higher water temperatures.

It is another object in at least one embodiment of the invention to enable winter sports in places that, without this invention, would have been affected by global warming. It is another object in at least one embodiment of the invention to prevent agricultural land and other land areas from being covered by water. It is another object in at least one embodiment of the invention to increase the survival of species that depend on large areas whit ice to survive, such as polar bears, penguins, and some seal species, and for a colder and more oxygen-rich water and promote species richness. It is another object in at least one embodiment of the invention that a comet or asteroid is captured and transported to an orbit between Earth and the Sun. And that substances to create shade, such as water, are retrieved from the celestial body and spread in the described way. It is another object in at least one embodiment of the invention to describe a method and process for creating shadow and at least one desired effect on shaded objects or areas. For example, regulate and in particular lower the temperature in air, soil or water and reduce the risk of ice melting, flooding, forest fires, whirlwinds or negative changes in life biotopes, or damage to electronics caused by solar storms. As well as reducing the number of cases of skin cancer in humans and animals and reducing the spread of desert areas. It is another object in at least one embodiment of the invention to enable life on Earth with existing species for a longer period than is possible if the temperature of the Earth is allowed to rise uncontrollably. It is another object in at least one embodiment of the invention to reduce or increase the shadow effect over specific areas, for example during the specific time of day and year. It is another object in at least one embodiment of the invention to describe how individuals can influence the degree of shadow effect across the area in which the person lives by voting for, for example, the desired percentage reduction in solar radiation, geographical location of shadow effect or equivalent, or voting for person and or computer programs representing the desired shadow effect. And the date and time the shadow should be applied.

It is another object in at least one embodiment of the invention to describe examples of how decisions can be taken and designed to create as few conflicts as possible and, for example, to determine when, where and how much shadow effect should be created on, for example, the entire illuminated part of the Earth during a specific period of time. Or one or more different geographic locations, where experts and computer programs first calculating the costs and effects of the options available at any given time for each said geographic location. Then, for each affected location, most of the population's said chosen desired shadow effect is also obtained. If the people's choice is in line with the experts' calculated and approved for a positive effect, then final implementation should then be determined in an international tribunal or similar with elected representatives and experts for the countries concerned. It also determines the costs to be paid by the various countries for, for example, operation and maintenance.

It is another object in at least one embodiment of the invention to describe a way in which countries that make money in different ways from a cooler climate are involved in financing the operation and maintenance of the apparatus and method based on the percentage estimated benefits of the countries. It is another object in at least one embodiment of the invention to describe a way for companies and countries to be able to insure against extreme weather and other consequences that the Sun can achieve if the spacecraft for creating shade is out of service. It is another object in at least one embodiment of the invention to describe a way in which, for example, countries or companies can insure, for example, an area or satellite from being hit by particles from a specific source or direction in space, such as particles from solar storms or known or predicted explosions in the universe. It is another object in at least one embodiment of the invention to describe a product in the form of a Sun barrier that shades an object or area from particles from the sun and produced in accordance with the method described here.

It is another object in at least one embodiment of the invention that one or more of the spacecrafts and cargo ships and tasks described in the invention and or tasks they perform can be insured against damage or interruption of said task, based, for example, on the estimated value of the work performed over a specified period of time, and or the cost of replacing each spacecraft or cargo ship with a new one. And where the premium per period can be determined based on both historical and estimated future downtime of the actual vehicle model, as well as where in the estimated lifespan each vehicle is located. It is another object in at least one embodiment of the invention that the distances are adjusted so that the Sun's gravity on the spacecraft to emit said Sun barrier corresponds to, and compensates for, the recoil from one or more laser cannons or equivalent particle accelerator intended to shoot particles at the Sun with the intention of colliding with photons and or other particles from the Sun. It is another object in at least one embodiment of the invention that at least one Sun barrier is placed at Lagrange point LI and is about 1/100 the distance to the Sun, and speed and foresight are continuously adjusted to the varying distance between the Sun, Lagrange point LI and Earth and the varying time it takes for different particles to travel from the Sun to Earth and that passes in the Sun barrier's orbit. It is another object in at least one embodiment of the invention that at least one spacecraft and Sun barrier in the form of at least one laser is placed at Lagrange point LI, L4 or L5 at Earth, Moon or Mars, but L4 and L5 are possibly today to far away from Earth.

It is another object in at least one embodiment of the invention that the invention includes computer programs on the spacecraft to send it to an orbit around the Sun, as well as computer programs to communicate via antenna between the spacecraft and the Control Center located on Earth when it is in said orbit around the Sun. It is another object in at least one embodiment of the invention that movable organs on the spacecraft can be controlled by the apparatus data unit and, if necessary, over -controlled or reprogrammed or updated via a data unit located at the said Control Center located on Earth. It is another object in at least one embodiment of the invention that the spacecraft is equipped with the corresponding technology and equipment used in lunar voyages, but adapted to carry, for example, ash in at least one container, and equipped with computer programs to automatically influence the spacecraft's jet engines to drive to in a computer unit programmed orbit around the Sun. It is another object in at least one embodiment of the invention that the spacecraft is equipped with computer programs, computer device and positioning/location equipment for automatic determination of speed, direction of movement/travel and precise position/location, as well as sensors for recording the Sun and Earth's location in relation to the apparatus, according to known technology used in space travel. It is another object in at least one embodiment of the invention that the spacecraft is equipped with sensors for monitoring all movable organs and the status of the spacecraft, and that said movable organs can be adjusted to the desired status or optimal status as necessary. It is another object in at least one embodiment of the invention to enable the spacecraft to dock with another spacecraft or cargo ship according to the method, process and equipment used by today's space shuttles docking with the ISS, or lunar lander docking with the launcher in orbit around the Moon. Where the intention is to be able to transfer, for example, fuel, substances to create Sun barrier and other supplies for operation and maintenance. It is another object in at least one embodiment of the invention that particles from the Sun hit generated radio waves, which are long wavelength light waves, before hitting the Sun barrier and that put the particles to be stopped in maximum vibration, causing them to occupy a larger surface area and increase the chance of contact with particles in the cloud that constitute the Sun barrier. Similarly, the particles in the Sun barrier can be exposed to vibrations that increase the chance of said particles from the Sun colliding and stopping. And created by speakers placed on the spacecraft.

It is another object in at least one embodiment of the invention that a laser pulse can be made to penetrate a medium that is converted into plasma, similar to the way that occurs when a laser beam penetrating the atmosphere, but where the plasma is part of the laser pulse that is pushed towards the Sun to increase the effect. It is another object in at least one embodiment of the invention that particles are prevented from hitting, for example, Earth by creating an artificial force field in a cloud of charged particles, such as iron shavings. Powerful magnets can be operated using one or more nuclear reactors. It is another object in at least one embodiment of the invention that substances are pushed towards the Sun by particle cannons that shoot small particles of matter towards the Sun, where the particles will collide with a large number of photons, where the particles can be accelerated with air pressure, explosives, lasers, or nuclear energy that, for example, can create a vapor pressure. It is another object in at least one embodiment of the invention that the particles pushed towards the Sun are electrons with a higher energy than the particles they are intended to stop, for example created by several powerful lasers or masers with optimized wavelength and with a wide beam. And is based on energy -rich particles from the laser colliding and stopping unwanted particles from, for example, the solar wind, or to create shade by hitting photons on their way to Earth. The laser is positioned so that it shoots into the path of the particles the user wants to stop, and if the distance to the Sun takes 8 minutes, even short laser pulses will collide with photons in said orbits for the said 8 minutes. Although, of course, both the laser and the Sun have moved during this time, the laser can be made to hit a stream of particles on its way to the object it wants to protect during this time. Despite this, relatively few particles are stopped by a laser pulse, which is why it takes a large bombardment against the Sun to have a measurable effect. This also means that it is not optimal to transmit all laser pulses in the same path, as some photons have already been hit by the electrons in front of the laser pulse. The effect increases if each laser spreads the shots, or shoots with a wide scattered beam with sufficient power to collide with said unwanted particles for as long as possible, and preferably throughout the journey to the Sun's surface. The overall effect on each laser beam is therefore higher than the aria on the laser beam at each distance. With a fixed obstacle, photons that hit the obstacle are stopped, but with an obstacle moving towards the Sun, photons will be stopped throughout the journey i.e., up to 8 minutes.

One advantage of lasers is that the effect stops completely after the last laser pulse hits the Sun, and that a limited area of specific coordinates can be protected by attacking particles in the direction of said area. While it is a disadvantage that it will take large amounts of power to power several lasers as well as rocket fuel to keep the laser guns in their orbits. And of course, also large amounts of the substances used to generate electrons. The laser can also shoot at an angle so that as much of the Sun's surface as possible is passed by the laser beam and made to collide with as many photons or other particles as possible heading towards, for example, Earth. The lasers can be placed on said device in the form of spacecraft orbiting the Sun and emit the laser beam across the Sun's surface in the direction of the Sun's far periphery so that the beam is not directed into free space. For example, the location can be at the very stable locations Lagrange point L4 and L5. When placing a laser or similar particle cannon at Lagrange point LI, several devices can be used and with a spread not exceeding the diameter of the Sun. The lasers can be powered by electricity from solar panels or nuclear energy. Recoil can be compensated by jet engines or by placing the particle cannon closer to the Sun so that the Sun's gravity corresponds to the recoil. Substances and materials required for maintenance for each specific type of laser must of course be transported to the respective laser from Earth as it is consumed. The speed of the movement of spacecraft with lasers in their orbit is adjusted and corrected with rocket engines, in this way known to satellites, so that they are always in the desired position and shoot in the desired direction towards the Sun, but where fine-tuning is advantageously done with electric motors and, for example, with sweeping motion and shoots line after line until the entire area of the Sun has been covered. Here, for example, equipment and technology for automatic cannons on ships can be used. There are several types of powerful lasers that can be adapted for the purpose, and which have been specially developed for military purposes, such as today's terrestrial lasers designed to shoot down missiles and satellites and intended for the so-called space defense, and drawings are available for a very powerful gamma ray laser. For this purpose, lasers/masers transmitting the beam with short pulses or continuously can be used, where wavelength and strength are adapted to the particles they are to stop. The laser pulse can also be made to contain other added particles, in this way known. And can also be made to penetrate a medium that is converted into plasma, like that of penetration of the atmosphere , but where the plasma is part of the laser pulse that is pushed towards the Sun to increase the effect. Russian scientists have developed lasers that effectively shoot through atmospheres, and which can also be used for the purpose described in this invention.

To achieve the desired effect against solar radiation to Earth, a sufficient number of lasers must be able to emit enough pulses, with a total average distribution over the Sun's surface, at least equal to the desired reduction in the number of particles hitting the object or area to be protected. The operation of the apparatus can be used with nuclear reactors, and for movements fuel is required for rocket engines, as well as electricity for electronics. The power can also be created with, for example, large solar panels, the power of which naturally increases if they are closer to the Sun. It is another object in at least one embodiment of the invention that the said laser cannon is equipped with safety systems that turn off the laser and block particles from being pushed in a direction other than the desired direction, if the device is turned from the target by, for example, recoil or if it is hit by a meteorite.

SUMMERY OF THE INNOVATION

Due to the enormous cost of implementing this invention and that it effects the whole Earth, I think a more detailed description of the effect is necessary and also different variants and aspects of these, and show that the effect can be controlled. And by shadowing the whole Earth it is inevitable with many effects on, for example, nature and life forms, hence the many objects described above. And if liquid hydrogen and oxygen are used as propellant, only water vapor will be dispersed into the atmosphere and the stratosphere when the large number of rockets are launched. One of the leading space companies now have spacecrafts that can lift 100 tons of goods into space and another company is developing very efficient hydrogen/oxygen rocket engines. And an even more efficient method would be if the first acceleration phase takes place in a vacuum tube, for example as described in the project called “Startram -maglev train” and provides a method to send substances in cargo ships to a low orbit, and from there, then load larger ships for transport to the location where the substances are spread. It is, of course, more efficient to manufacture on site and it’s just a matter of time before most things will be manufactured in space, as needed. And means that the substances can be manufactured in space, or as a by-product of manufacture of other products, goods or chemicals intended for transport to Earth, the Moon or Mars and where the waste can be used to produce a Sun barrier.

To reduce solar radiation by a certain percentage to the whole Earth, it is an advantageous to locate one or more obscuring obstacles between the Earth and the Sun, and preferably around the Center of the Sun, where then the size of the Sun barrier is adjusted so that it obscures the desired percentage of the Sun for an observer on Earth. Put simply, this means that if the Sun barrier covers one percent of the Sun's surface at the selected distance, the solar radiation to Earth will decrease about the same amount. If a user wants the same percentage reduction but use smoke, water particles or the like and which are spread like clouds, then the size of the cloud must be increased if some photons can pass the Sun barrier. For example, if the cloud lets 50% of the particles through, the cloud's surface must be doubled compared to if it was impenetrable. I suggest that the Sun barrier is placed at Lagrange point LI for clouds and where it will stay for a long time du to gravitational influence, and not obscure the Moon or travelers between the Earth and the Moon or Mars. Expects that it will take at least 10 million kilos of, for example, fine-grained coal or ash to obtain a measurable positive effect. And to create the desired cooling effect, the said measurable amount is of course required several times. And if the substances spreads evenly and in the optimal direction and speed, then a flat circular cloud can be made very thin and with high effect, while the cloud remains in the orbit for quite a long time. For example, if it spreads 0.1 kilo per 10 square meters, it corresponds to 100 kilos per hectare, and 1 million kilos per square mile or 100 square kilometers.

The proposed amount could theoretically cover around 10 square miles, but such an even and thinly distributed cloud is of course not possible to create with the forces acting on the individual particles that will travel towards the periphery and eventually thin out. If a spacecraft can load 20 tons, the cost today for transporting 20 tons to said orbit would be about $ 200 million and for 500 rides would be an additional total cost of about $100 billion. And by comparison, it is about 100 times more than what Sweden gives in aid to other countries annually, which is why the sum must be divided between several countries. And the money it costs is not sent into space, only several million tons of ash or equivalent. I suggest starting with an experiment with a calculated measurable cooling effect and gradually, with the guidance of measured values, increase the amount of spread substances until the desired effect is achieved. I believe that starting on a small but measurable scale will increase confidence in the idea, and the global trust and willingness to implement the project on a full scale. And by comparison, in the event of a solar eclipse, the Moon covers an area of approximately 94 896 square miles or 9 489 632 square kilometers, and the shading effect of a solar eclipse is of course known. But the good thing is that only a fraction of this effect is needed to obtain a positive effect on Earth. And the test of a space barrier of 10 square miles proposed here should be seen as completely harmless and is about ten thousandths of the area of the Moon, and four times as far away, and let through most of the Sun's rays. A problem also poses the large distance and consumption of energy for launch, as well as acceleration and deceleration of the spacecraft sent to and from the Sun barrier orbit, where, for example, it takes about three days to travel to the Moon and which represents about a quarter of the distance to Lagrange point LI. But in space, distance does not mean that fuel consumption needs to increase. If the spacecrafts take twenty tons, it will take about five hundred journeys to build up a large enough cloud of this proposed ten million kilos and must then be maintained. But the cost must, of course, be set in relation to the costs and dangers that the Sun barrier can prevent. And that the whole world will benefit from the effect and, hopefully, want to share the cost. Earth's orbit around the Sun is about 940 million kilometers, and the orbital speed is about 108,000 km/h and moves about 12,700 kilometers in 7 minutes, which corresponds to an Earth diameter. And means that even photons that travel at the speed of light and leave the Sun at any given moment in direct direction to Earth will miss Earth, as the photons' journey takes about 8.5 minutes. Why, for example, the photons to be reduce in number must be attacked with foresight in the direction of movement of the Earth and adapted to the speed of the Earth and the time taken for the journey of particles from the Sun to what is to be protected. And that one or more Sun barrier is placed in the calculated path of said particles and the foresight is determined by the distance between the Sun barrier and, in this example, the Earth. So that the obstacle reduces the number of particles travelling in said path, in the direction of where the Earth is when the stopped particles would have arrived. Where the size of the Sun barrier must increase with increasing distance to Earth to obscure the same amount. Where also the type of particles that are primarily to be reduced can be regulated with the choice of substances and the density of the Sun barrier, since different particles from the Sun have different abilities to penetrate different matter and densities. A separate orbit around the Sun means that said spacecraft and the physical Sun barrier orbit the Sun and that the distance to what is protected, such as the Earth, is large enough to prevent anything from the spacecraft, such as smoke or chemicals being drawn to Earth by Earth's gravity or to the Moon by the Moon's gravity. The intention is to avoid that said substances used to achieve the desired effect from entering the Earth's atmosphere, and by giving it a speed in said direction, it acts as a Sun barrier for a long time compared to if it stood still due to the speed of Earth. By choosing substances and density, the Sun barrier can be made to function as a sunscreen that lets through particles with the desired wavelength and reduces particles with unwanted or harmful wavelength. Another advantage of spreading substances between Earth and the Sun is that the Sun barrier can be designed with a desired percentage shaded effect all over the Earth, compared to when spreading in the atmosphere, where the substances used must be spread throughout the Earth to have the corresponding effect. The effect of the Sun barrier is regulated by changing the area and or density of the substances and where, for example, a percentage of the Sun is shielded with said substances and where the deployment/spread is done using said spacecraft. For example, the cooling effect can be increased with larger and or denser clouds of, for example, ice crystals, ash, dust/smoke particles or more or wider and more powerful laser beam. By laser is meant manufactured particle current with a higher energy than the particles the user want to stop and includes colored light- absorbing light as well as charged particles of different wavelength and energy content. To reflect photons and other radiation from Earth, bright particles are considered to work best, but expect that as black particles as possible are preferable when dispersing into space, such as clouds of atomized carbon or ash. Because dark particles do not reflect photons between the individual particles in the cloud or in the direction of Earth, at the same time as the clouds that will inevitably become hanging after at some time will not be visible from Earth. Also, chemicals and other substances suggested for use in the Earth’s atmosphere can be used in space. The means and method allow for a desired percentage reduction in solar energy, such as a 2% reduction over the whole Earth or a large sea area. Or, for example, a 5 % reduction in solar energy for both polar regions and, for example, a 7 % reduction to a desert area. This is achieved by calculating the particle obstructive effect of the substances to be used and calculating the shape, size, and density that one or more, here called Sun barrier, must have at a specified direction and speed, and at a calculated and determined optimal distance from Earth in order to achieve the desired effect.

The spacecraft can be designed to produce and spread reflective, absorbent, and obstructing particles, for example smoke from combustion, dust of matter, chemical reaction, or steam, especially water vapor which freezes to ice crystals when the steam is expelled from a heated water container in the spacecraft. And which, depending on the chosen density of the cloud, prevents the chosen proportion of solar energy from reaching, for example the Earth. And, as an example, so can water be made to boil at 20 °C in vacuum. And one liter of water can be converted into over 1000 liter of water vapor at the air pressure of one bar and will expand in all directions when it is transferred to the vacuum of space via the nozzle. And each water molecule will freeze to an ice crystal and a cloud is formed. Water that freezes without added gas will be quite transparent, so it is an advantage if the water molecules are mixed with gas molecules in the container and, when sprayed out through the nozzle, will be both larger and less transparent. Evaporation of water in containers can be done by means of, for example, heating elements or with microwaves powered by so lar cells or nuclear reactors, where the steam is expanded to an overpressure by monitoring and controlling the boiling process, and then sprayed out via electrically heated nozzles in the desired directions and the desired amount to create a cloud of the desired size, shape, and density in the location of the spacecraft at any given time.

The spacecraft can also be designed with a snow cannon, using known technology but where the growth of ice crystals takes place inside the spacecraft, and with overpressure then blow out the crystals and create a snow cloud that moves in orbit around the Sun, where more snow is produced as needed. If the snow is given a different speed or direction than the calculated path to create shade in the desired location, then the thinning of the cloud must be continuously compensated. The spreading of particles can be done with a pump or a rotating valve with at least one opening that spreads the particles in a circle, where the particles at as low a speed as possible float towards the periphery and gradually thin out. The particles can also be spread in at least two opposite directions with the same force and quantity to equalize the forces that may affect the desired position of the spacecraft. Furthermore, user can control the direction and speed the particles leave the spacecraft, which controls how the cloud of particles lies in relation to the orbit around the Sun in which the spacecraft is located. Furthermore, particles from solar storms normally travel at significantly lower speeds than light, which means that a Sun barrier for these particles must be placed with a foresight adapted to the speed of the particles and the location of the Earth when they would reach it. Thus, the Sun barrier must be placed somewhere in this orbit where these particles are expected to pass. Furthermore, several spacecrafts are preferably placed after said line in orbit around the Sun, but at slightly different distances from that to be protected and can complement each other's effect or compensate for the loss of any spacecraft. And the spacecrafts can fly in any mutual formation that proves effective when spreading substances. The spacecraft requires continuous supplies of consumables, which can be transported from Earth or other celestial bodies such as the Moon, Mars, comets, or asteroids. The launch of the spacecraft and supplies to the appropriate orbit can of course take place with, for example, well- tested rockets used, for example, to launch people and supplies to the space station. And the spacecraft can also be equipped to carry paying passengers to the spreading location, here also called place.

A computer unit, here also called a controller, calculates and controls the speed, direction of movement and the position of the spacecraft in a location stored in said computer unit The spreading location can be placed between the Sun and the object or area to be protected based on, for example, the determined location for an object or area to be protected in a location system, for example a coordinate system including the Sun, for at least the time the spreading is determined to start. And the determined distance between the sun and the orbit around the Sun for the protected object or area, and the direction of travel for the object or area in its orbit and the speed for the object or area. And also, the speed for at least one type of particles from the Sun is determined in order to determine the time it takes for the particles to travel from the Sun to the object or area. And determine if the particles travel time means that the Sun barrier must be located with a foresight on the determined distance between the Sun barrier and the protected object or area. And determine a designated spreading location(s) for at least one type of substances for creating at least one Sun barrier in said orbit around the sun where said particles from the Sun is determined to pass. And adjust/change the speed and direction of travel for the Sun barrier in its inner orbit to the speed and direction of travel for the object or area in its outer orbit around the Sun in order to maintain the distance and location between the Sun and the object or area. And based on the speed of the particles to be reduced/stopped, determine how long time it takes for the particles to travel between the Sun barrier and the object to be protected. And determine how far and in what direction the object will move during this specified time. The speed of particles leaving the Sun can be obtained from the satellites that continuously monitor the Sun using, for example, lasers and radar and camera equipment.

If only parts of an object are to be protected, it is also determined whether the object rotates, direction of rotation and speed of rotation, and determine whether the Sun barrier must change direction of movement and or speed due to the rotation of the object. And based on the information, it is determined how far in front of the object's one or more Sun barriers at each point must be in order to continuously protect the selected area. The Sun barrier can thus be placed between the Earth and the Sun and reduce solar energy from warming the entire Earth or selected areas of the Earth, such as the North and South Poles or, for example, sea areas where hurricanes draw energy from warm seawater. When a specific area of earth is to be protected, this is facilitated by the use of several spacecraft, which are placed in slightly different orbits around the sun, and which spread substances when particles from the Sun are moving towards said protected area. And where said substances that spread quickly dissolve so as not to continue to shade other areas. Can also reduce the intensity of local whirlwinds and forest fires or prevent local glaciers from melting, and place countries in continuous darkness in case of conflict, for example Sweden if they are serious about the threat to restrict freedom of expression.

For the spacecraft to have a stable trajectory and reduce the impact of gravity on, for example, generated smoke, snow or ash, the spacecraft can be placed near the said Lagrange point LI between the celestial bodies about 1.5 million kilometers from Earth and one hundredth of the distance to the Sun. Gravity from the two celestial bodies takes each other out there and objects located in this area will in this example have the same orbital time around the Sun as the smaller celestial body but, of course, at a slightly lower speed. If a very large cloud is needed, parts of the cloud may end up outside the area and be affected by gravity. Due to the need for foresight, the obstructive agent can be placed at the leading edge of Lagrange point LI in the direction of movement. The extent of this point depends to some extent on which of the theories of the effect of gravity that is correct, where it is considered by some scientists that each celestial body creates a bulge in the universe which then affects other free-flying objects. While others believe that gravitons work more as magnets and pulls on the objects themselves, and where gravitons act with a time consumption corresponding to the speed of light, in this case 5 seconds. While the rubber cloth theory is usually described as a direct-acting wave motion. In the case of said colliding gravity from the Sun and the Earth, the exact length and location on Lagrange points should indicate which theory is correct. Furthermore, said Control Center that monitors the entire process is located on Earth and equipped to send commands to the computer unit on the spacecraft with information from sensors on Earth that continuously measure, for example, light permeability and thus the shading effect of the Sun barrier on, for example, different areas of the Earth. And of course, the spacecraft is also equipped with sensors and equipment to transmit the desired information from the spacecraft to said Control Center.

Sensors for measuring the particle current desired to be reduced are also advantageously placed on satellites between the Sun and the Sun barrier and between the Sun barrier and that to be shaded, and of course on the coordinates to be shaded. And if the user wants to measure if only the selected area is shaded, then sensors are also placed outside this area. Furthermore, the spacecraft must adapt to the varying relative velocity of planets orbiting the Sun when they have an elliptical orbit, for example the Earth, where the velocity is experienced more slowly when the planet also moves from or towards the Sun. It may therefore be required that the size of the Sun barrier must be increased or decreased if the same size of the protected area is to be maintained, and that the speed of the spacecraft in its orbit around the Sun can be adapted to the actual movement of the planet. When the distance between the planet and the Sun changes, the time it takes for the different particles to reach the planet also changes, which is why any foresight must also be adapted if the exact same area is to be protected. Where the foresight for photons is just over one Earth diameter when placed close to the Sun and when placed in the immediate vicinity of the Earth where it only takes a few seconds for the particles to travel between the Sun barrier and the Earth, no foresight is needed unless the boundary must be very precise. From Lagrange point LI, it takes 5 seconds for photons to reach the Earth and up to an hour for the slowest particles from a solar storm. The spacecraft is then controlled so that the desired area is shaded for the desired period, which is done by placing the spacecraft in orbit around the Sun and, if necessary, moving it with rocket engines so that it is always in the desired location between the Sun and the Earth. With an foresight corresponding to the time, it takes for the specific particle, such as photons, to pass the Sun barrier and reach the Earth, and the distance the Earth has moved during this time of up to about 8.5 minutes if the Sun barrier were located at the surface of the Sun. And where the size and shape of the shadow created against the Earth is mainly determined by the substances of the Sun barrier, and the size, shape, angle of the Sun barrier. And the angle of the Earth to the shaded area, as well as possible light permeability and the actual but varying distance between the Sun and Earth. And, of course, also the distance of the Sun barrier to the Earth.

If the size/position of the Sun barrier means that the area to be shaded is not greater than that any part of the Sun's surface can continue to illuminate the shaded area, then of course the area will be Sun-lit, but with reduced solar radiation, which is of course also the preferred solution. And because it is not possible to look directly at the Sun, the spacecraft and substances used will not be visible to the naked eye. And if the Sun barrier is placed at a distance from the Sun where it takes 8 minutes for the photons to reach, then the Sun barrier from the Earth will be perceived as being located where it was 0.5 minutes before the particles would have hit the Earth. This means that if a specific area is to be completely put in the dark, then the Sun barrier must shade the entire surface of the Sun that can illuminate this area and means that a very large area outside the treatment area will be shaded. In order for the Sun barrier to be used against particles from solar storms, the Sun barrier must be placed with significantly longer foresight because the particles in question travel at a lower speed than photons. Alternatively, that the Sun barrier is placed very close to the Earth, which should be avoided. Furthermore, a Sun barrier will block different amounts of particles with a direction to Earth depending on where on the Sun's surface it obscures. Depending, for example, on the fact that the Sun's temperature and activity vary greatly, and that particles from the Sun's periphery that are blocked in certain situations would still not hit Earth, for example if the Sun barrier were to be placed far back on the Sun in the direction of movement.

The amount of substances used to create shadow is practically fine-tuned using information from censors. For example, by collecting quantities from a plural of sensors measuring temperature and or particle current from the sun which records the amount of particles that reach what is protected. The information of one or more of the said censors is equipped for data transfer of registered quantities to a Control Center located on Earth where collected quantities are compared to the desired values stored in an evaluation means in the form of a computer unit comprising a controller. In case of deviation from the desired value, it is determined how much substances are needed to achieve the desired value and whether the amount of substances should be increased or reduced. The control Center then transmits data wireless and command to at least one automatic flying spacecraft to adjust the amount of substances to spread to the decided new level. The spacecrafts controllable means can be monitored, oversteered, and remotely controlled/supervised from said control center. And by collecting data quantities from radar sensor units for measured size and density on the sun barrier and which are placed on Earth and or on spacecrafts. The Control Center can determine the shading/obscuring effect at any given time by analyzing the collected data from sensors placed on the object or area and censors placed on spacecrafts or other satellites. And compare the stored desired obscuring effect with the actual measured effect and, in case of deviation, calculate how much substances need to be spread to achieve the said desired values; And, sending control signals to one or more spacecraft to correct the amount of spread of substances to the new value; And, use of the actual calculated shade effect and the effect of the planned spread of substances to calculate the total shading effect over a period of time; And, use the total value from said calculated shading effects to calculate weather forecasts for all or part of an object or area.

When using smoke, it is an advantage if the particles do not dissolve and separate to give the desired effect for as long as possible. Lasers or other types of particle guns can be placed in the even more stable orbits at Lagrange point L4 and L5. And is in the same orbit as the Earth, but due to the enormous distance to L4 and L5, the supply of necessary substances is made more difficult. If gases are used to create a Sun barrier, it is an advantage that the gas can be transported in liquid form while it is a disadvantage that it must be continuously replaced to compensate, for example, for what is called Brownian motion between the particles, and that the gas will be ionized by the solar wind. The gas will then be tightest at the point where the gas is emitted and gradually thinned out towards the periphery and driven away from the Sun at an accelerating speed. Slightly larger particles such as ice crystals, ash particles or snowflakes may therefore be more effective. Of course, it is also an advantage if the substances are so small that they cannot damage, for example, solar panels or satellites in the event of a collision. Smoke can also be produced in many ways with different substances that oxidize or can otherwise be made to react with each other, and in, for example, oxygen-poor combustion of most substances, large amounts of smoke are formed, and the corresponding effect can also be created by reactions between a variety of other substances. For example, the combustion of various rubber mixtures is known to produce huge amounts of black smoke, where of course the spacecraft must be equipped with an oven and regulated input of what is to be burned, as well as oxygen and automatically controlled regulator to regulate the emission of the smoke. For example, ash from combustion on Earth can also be scattered in the orbit around the Sun and could then be sent up vacuum-packed and compressed and torn up by a rotating knife or drum before spreading. If a spacecraft with, for example, said ashes travels at this distance and in the same direction and speed the user wishes the ashes to have and if, for example, 14 kilograms of ash is scattered per minute, then it would take 24 hours to spread 20,160 kg and would be a possible load for a spacecraft. The individual ash particles will aim to maintain the same position and speed between Earth and the Sun due to the gravitational forces at Lagrange point LI, which are determined by Earth's speed. Although the ash particles are of course affected by the solar wind and the speed and direction of the discharge from the spacecraft, as well as inter -gravity and collisions. In order to have any measurable effect, a tight obstacle must also have an area of several square miles at this distance, and in order to build up a sufficiently large cloud, several spacecrafts should of course be used. Another option is different types of chemical grenades, thermite grenades and especially military variants of smoke grenades that can also include a multi -spectrum component to make the smoke IR impermeable. These grenades form large amounts of smoke and are emitted via holes in the grenade and there are variants that are activated with a small explosive charge for faster effect. There are also substances that emit more smoke than those used in the above-mentioned applications but are not used because they do not want to spread toxic substances on Earth. For this purpose, a variety of components can be used, but must of course be adapted to the vacuum and weightlessness of the universe as well as the lack of oxygen. When incineration is in place in the said orbit around the Sun, oxygen can be carried and supplied when oxidation/combustion of the substance that produces smoke. And where all forms of expansion and explosions mean that the Sun barrier, such as the cloud of smoke, is rapidly thinning out. For example, if a user wants to reduce solar radiation by 2% and use particles that are affected by Brownian motion and thin out towards the periphery, the effect will still be over a longer period of time than when the cloud area corresponds to 2% of the Sun's surface. Because even some photons will hit these scattered particles, as long as they are in the actual orbit between the Sun and where the Earth is when the photons would arrive.

It can be a problem to spread said substances in weightlessness without giving the particles a different speed than the desired path speed in the orbit, where the problem can be reduced, if necessary, if the spacecraft that spreads the particles waiting for the optimal location in the said orbit for dispersion. Where the speed of the spacecraft plus the speed at which the particles leave the spacecraft in the direction of movement, together corresponds to the optimal orbital speed. Alternatively, the spacecraft travels slightly faster than the desired orbital speed and the particles are spread out backwards at the same speed as the spacecraft exceeds the desired orbital speed. For example, the ejection/ spreading of said substances from the spacecraft’s storage container can be done through an electrically controlled nozzle, where gas from a gas cylinder creates an overpressure in the container and pushes out said substances at a specified pressure and speed. The container can also be equipped with a rotating fan or knife to allow solid particles such as ash or carbon to be spread evenly through said nozzle. Where the amount of agent dispersed in this example can be regulated by the air pressure in the container as well as the shape and opening degree of the nozzle. Said containers are also equipped with a refill hatch for said substances. And, depending on the substances used, also, for example, combustion chambers and containers for the substances needed in the specific design. As well as computer programs for controlling the specific tasks required by each input subject. For example, when ash is dispersed in a vacuum using gas, the expanding gas will facilitate a plume-shaped scattering of the ash. The Cargo ship carrying said means may also be equipped with organs and computer programs to carry out the spread itself or equipped with coupling organs to be connected to a separate spacecraft to spread the substances and can be spread by, for example, compressed air. Another option is that the container consists of a rotatable drum, which, at the time of distribution, is set in rotation at one revolution per minute, and with the flat sides of the container facing the Sun and Earth. Then an electric motor pulls the round part of the container aside and exposes the contents, where the very slow rotation gives the particles in the said substances a low speed obliquely outwards, creating a circular cloud that will gradually thin out. The container can also be designed as, for example, said smoke grenades and released from the spacecraft at the desired location, direction and speed and independently perform the spreading, and the spacecraft can return to Earth direct to pick up a new load. The substances that are dispersed will gradually thin out and must be continuously compensated for. If the calculated daily need for substances corresponds to what a driverless freighter can transport to Lagrange point LI and that a round trip will take under a month and that service and replenishment of particulate substances, take another month. This will be a two-month orbital period for each cargo ship and these conditions will require 60 cargo ships in continuous operation, as well as additional cargo ships to create a sufficiently large cloud. But this is determined, for example, by the shadow effect wanted and what substances is used to create shade, as well as the speed and size of the cargo ship. And if the cargo ships are filled when they are in an orbit around the Earth or if they must land. The most effective method is to build very large cargo ships that do not have to return to Earth and are serviced, refueled, and filled in space, and provided with organs to be able to spread said substances from said orbit around the Sun. And which is loaded with the help of a fleet of lighter craft, and which are retrieved from Earth, the Moon, or Mars.

We should also look for asteroids and comets that can be captured and transported to the optimal location to extract selected matter and then disperse/spread the substances. If said asteroid or comet is placed in said orbit, it will constitute an almost insignificantly small particle barrier, but by, for example, evaporating and atomize the components, smoke, gas, dust and other reflective or absorbent particles can form of all matter. This invention does not, of course, solve the problems of today's emissions of pollutants into the atmosphere, which must be drastically reduced. And the most effective way would be to build enough nuclear power stations and use the heat from volcanic eruptions and more solar panels to generate an excess of electricity, and then offer consumers electricity at the lowest possible cost, thus competing out environmentally destructive alternatives. For example, electrical cables can be laid from Iceland to Europe and North America.

And because of the fact that Earth will be in trouble when the magnetic poles change direction, a solution needs to be in place when this happens. The sun will also gradually increase its energy release, which is why in the long term it will get warmer regardless of the state of the atmosphere. And the warmer climate we are already experiencing, for whatever reason, means that it would already be a great advantage if we could reduce solar radiation slightly to reduce the increasingly powerful natural disasters we are experiencing around the world. Although this proposed attempt to spread substances between the sun and earth is costly, it may be the salvation if other earth-bound measures do not have the desired effect, which they will most likely not have. The proposed invention, on the other hand, will have many positive side- effects, such as jobs for the manufacture and maintenance of spacecrafts and for all space travel technologies and for several space companies to be commissioned in space, which will reduce the cost of space travel. The different variants of spacecraft described here can also be equipped with space for passenger transport for paying guests in addition to their other duties. It should also be added that if liquid hydrogen and liquid oxygen is used to the rocket engine, the only residual product becomes water vapor. This would mean that the many launches of spacecrafts will not pollute the Earth's atmosphere.

The invention possesses numerous benefits and advantages and when less ice melt and the water get colder that also mean that fewer areas will flood and force people to move. At the same time, cultivation is facilitated and reduces the risk of crops being destroyed by extreme weather and means safer food supply, while the invention can make people realize that they must work together to resolve major disputes, and work towards a common goal for the entire planet. The cooperation required on this invention can therefore also help to resolve future wars and conflicts. LIST OF ELEMENTS IN AT LEAST ONE EMBODIMENT:

Here numbered as in system 200.

I. Control Center. Monitors and controls the entire fleet of ships and continuously monitors the effect of shading on the objects or areas protected, and, if necessary, changes the work carried out to achieve the objectives set as effectively as possible. Placed on Earth and, monitors and influences spacecraft 3 and Cargo ship 23 and collects and processes information from Censor 31 regarding the measurement of specific particle current from the Sun and or its effect on object or area 25, in particular temperature.

3. Spacecraft. Flying Craft to transport and spread substances 27 and 19 and create Sun barrier 29.

5. Radar. Radar unit. For example, a doppler radar for determining Sun barrier 29 in terms of size, density distribution, shape, and the like in order to calculate the effect. Can also be supplemented with camera systems. Can be placed on a spacecraft and/or on a planet, for example the Earth.

7. Rocket engine. Refers here to both transport rockets and several small rockets for position corrections and comprising a sensor for registering the amount of fuel in the fuel tank.

9. Container. To store and transport of substances 27 or ingredients or consumables. Can also be supplied with heating means 11 to vaporize liquid, such as water, and create an overpressure that can be used to spread agents/substances via nozzle 17. And comprising a sensor for registering the amount of substances in the container.

II. Heating means, placed in the container 9. For example, microwaves, heat spirals or lasers to prevent substances from freezing and, for example, heat or vaporize liquid in Container 9 and also heat the nozzle.

13. Gas crane, connected to a gas tube, in this example an oxygen tube. Add oxygen to the combustion chamber 21 and or create overpressure in containers 9 to push out substances through, for example, nozzle.

15. Spreading device. Device for transporting substances out of the container 9, for example a pump, a vibrator, a rotating knife, which can also act as a fan, gas or, for example, a screw to bring substances 27 from the container 9 to an inner orbit around the sun, via nozzle 17, and were said nozzle 17 can be placed on a Laser 19 and spread the laser beam.

17. Nozzle. Dispersing/spreading substances, and also substances in the form of a laser beam and designed in different ways depending on the type of substances 27 to be spread, can also be electrically heated to prevent liquid from freezing, and is designed and dimensioned to the selected substance to be distributed by each spacecraft and the amount per unit of time to be dispersed/spread. And can be designed so that the degree of opening and the direction of spread can be adjustable with electric motors. One or more nozzle can also be made movable and can be directed in different direction and used in the same way as rocket engines to adjust the spacecraft speed an direction of travel.

19. Laser, electrons etc. are spread via a nozzle 17 and create a particle pulse or beam, where several lasers are directed towards the Sun, for example from Lagrange point 1, 4 or 5. Can also be placed closer to the Sun where the Sun's gravity corresponds to the recoil.

21. Combustion chamber. Comprising heating means, for example a radiator or microwaves to create smoke by oxidizing matter or chemicals. 23. Cargo ship. Transport supplies to Spacecraft 3 and can also be designed to spread substances 27 from an inner orbit 43 around the Sun and be equipped as spacecraft 3.

25. Object or Area. Refers to what is protected by a Sun barrier 29. For example, coordinates can be given in a coordinate system that includes at least the coordinates in the universe where the Sun and said objects or area, as well as apparatus/spacecraft 3 will be during the time that Sun barrier 29 will prevent particles from the Sun. Since the Sun moves in the Galaxy and the galaxy moves in the universe at a tremendous speed and also rotates, of course said coordinate systems should not cover more than our solar system, and where the Sun is given a fixed point with distribution in the coordinate system. And then, preferably, put a fix point in a distant star in the Milky Way, if the fix point is set in another galaxy, the margin of error increases over time. There then planets and satellites move in this fixed coordinate system around the Sun.

27. Substances. Here called substances can be anything that can block said particles from the Sun and consist of an organic substance and or inorganic substances in any color or colorless or combinations and forms, for example, electrons in laser beams, smoke, ash, carbon, water, smoke grenades or a mixture of chemicals. And where the ash may include ashes from deceased person or pet. The density and type of used substances can also act as a sun cream and lover the amount of a specific type of particles from the Sun determined to be, for example, dangerous.

29. Sun barrier. An obstacle used to stop or reduce the amount of particles from the Sun and created of substances 27.

31. Censors. Placed at the object or area being protected or placed on a satellite flying between the Sun barrier 29 and the Sun and the Sun barrier and said objects or area 25, recording, for example, the amount of particles before and after passing the Sun barrier for determining the effect. Measured values are sent to control Center 1 for further evaluation, can also include cameras of different wavelengths and Doppler radar and similar weather apparatus. For example, if the temperature is higher than a specified desired temperature, the said Control Center 1 sends control signals to one or more spacecraft 3 to change the amount of spread substances 27 to a new value.

33. Censors. Placed in the spacecraft 3, the status of all the organs and functions of the spacecraft are continuously monitored and is linked to the spacecrafts computer unit which, for example, automatically corrects the abnormal values to in the computer unit stored, and the information from said sensors is also passed on to the Control Center 1. All of the means in this invention are monitored by censors and to what extent they are, for example, activated, operational, and record measurable settings, filling rates, temperatures, pressures and the like.

35. Nuclear reactor. Nuclear power plant, a closed system for the operation of a generator for electricity generation.

37. Solar panels. Generate power for operation of the spacecraft and store power in battery.

39. Transmitter / Receiver at the Control Central 1, for wireless information exchange with spacecraft 3, and other vehicles as well as weather and news stations.

41. Transmitter / Receiver at the spacecraft 3 and cargo ship 23 for wireless information exchange with Control Central 1, and other vehicles. 43. Inner orbit around the Sun, here means an orbit in the vacuum of the universe around the Sun with the same orbital direction as that to be protected, and with placement and speed adapted to what is protected.

So that the substances 27 that is spread to be said Sun barrier 29, can be placed so that a certain amount of particles from the Sun that are headed towards what is protected, must hit the said Sun barrier 29.

45. Outer orbit around the Sun, such as the orbit to Earth, the Moon or Mars, but it can also be satellites or another spacecraft. An outer orbit can also be a route to, for example, the Moon or Mars.

47. Computer program located on Control Center 1. Computer programs and the necessary equipment for monitoring and controlling spacecrafts are known technologies, therefore only features specific to this invention are described here. Computer programs with stored preferred and desired values for, for example, temperature or particle current from the Sun at a specific geographical location at a specified time, and the measures to be taken at different thresholds if the measured actual values are below or exceed the desired value. Said value is advantageously an average of a large number of censors spread throughout the protected area. For example, a Computer unit calculates incoming quantities from censors and correlates with said stored desired value, and in case of deviation greater than at least one of the said thresholds, control signals are sent to at least one spacecraft 3, with a new value for the spread of substances 27.

49. Computer programs placed on the spacecraft 3 with transmitter receivers for communication with Control Center 1, as well as functions to control and activate organs and functions of the spacecraft 3, and position themselves in relation to, for example, other spacecraft or Cargo ship 23. However, as this is known from today's spacecraft, this is not described in more detail. It therefore describes only functions specific to spacecraft with tasks described here. In particular, it is possible to send and receive information to determine the speed and direction of flight on the basis of said object or area 25. And to control the amount of said substances 27 by, for example, activating the nozzle 17 to a specific position in a specified location for a specified time. As well as pointing a laser 19, towards the selected area of the Sun and shooting at the desired range and, if necessary, correcting the position of the spacecraft 3.

51. Computer unit. Placed at Control Center 1.

53. Computer unit. Placed in Spacecraft 3.

55. Location sensor. Position determination system, for example GPS.

57. GPS satellite, or equivalent system. And advantageously equipped with Censors 31. One or more can also be equipped with Radar Unit 5.

59. Schematic view of funnel-shaped travel path for particles having specific velocities, and which at this moment starts the journey from the Sun and indicates here where the earth is located at this moment. And where the Sun barrier 27 must be placed to be able to stop the specific particles. Does not apply if the Sun barrier 27 is close to Earth, or when using the laser 19 which can shoot from all angles and distance. BRIEF DESCRIPTION OF THE DRAWING

I Fig. 1 A shows a schematic view of an apparatus for spreading substances and a created Sun barrier and the funnel-shaped particle stream for, in this example, photons leaving the Sun at any given moment and where the Earth is located when the photons travel begins, and means that when placed near the Earth, the sun barrier can be placed on the side of the funnel-shaped particle stream.

Fig. 2A shows a schematic view of Lagrange points for Earth, and the preferred location LI;

Fig. 2B shows a schematic view of a spacecraft for spreading substances and laser beams.

FIG. 3 is a block diagram of electronic circuits included in one embodiment of a spreading and mapping spacecraft supervised and controlled from a control center on Earth.

FIG. 4A is a Sun barrier detection and spreading system according to an exemplary embodiment. FIG. 4B is a block diagram of a controller of the Sun barrier detection and spreading system.

FIG. 5 is a flow diagram of a method of mapping Sun barrier characteristics and spreading substances according to an exemplary embodiment.

FIG. 6A is a stand-alone Sun barrier detection and mapping system according to an exemplary embodiment.

FIG. 6B is a block diagram of a controller of the stand-alone Sun barrier detection and mapping system. FIG. 6C is a flow diagram of a method of mapping Sun barrier characteristics according to an exemplary embodiment.

FIG. 7A is a stand-alone spreading system according to an exemplary embodiment.

FIG. 7B is a block diagram of a controller of the stand-alone spreading system.

FIG. 7C is a flow diagram of a method of spreading substances according to an exemplary embodiment. FIG. 8 is an Earth-based Sun barrier characteristic detection system according to an exemplary embodiment.

The Sun barrier system 200 will now be described. Referring to Fig 1, 2A and 2B. The sun barrier 29 intends to reduce the amount of one or more type of unwanted particles from the Sun and protect an object or area 25 from especially heat related damage and disasters, but also damage on electronics. And first a short description of preparation; The preferred reduction in solar radiation is determined and given a value and threshold values for when specific action should be taken and stored in a storage device coupled to a controller. The location in space for the Sun and the object or area 25 is determined in a coordinate system and also the orbital distance to the Sun, direction of travel and speed. And also, the speed for the particles to be stopped, and determine an orbit to place the Sun barrier 29 and its direction of travel and speed in the chosen orbit. And chose the type of substances 27 to use to create the Sun barrier 29 and the amount needed to create the determined value for shad effect. A control Center 1 placed on Earth control and supervises the whole operation, and in shown example the Earth is protected and the sun barrier 29 can also be made to protect satellites orbiting the Earth. spacecraft 3 is assumed to use rocket engines 7 and a pre-programmed computer program 49, not shown, to automatically move from a launch site on Earth to a specific inner orbit 43 around the Sun, for example, Lagrange point LI, and Lagrange point L4 or L5 for laser canon 19 or other particle canons. And the travel path for each type of particles planned to be stopped is determined and is here shown as a schematic view of funnel-shaped travel path 59 for particles having a specific velocity, in this example photons, and which at this moment starts the journey from the Sun and indicates here where the earth is located at this moment.

The controller in a computer unit 53, not shown, in the spacecraft 3 automatically controls, navigate, steers and adjust speed and direction of travel to the stored instruction and coordinates in the computer unit 53, storage unit, and places itself in the pre-programmed inner orbit 43 around the Sun and at said specified direction of travel and speed. Determined by the speed and direction of travel of the object or area 25 to be protected, in its outer orbit 45. As well as the chosen distance between the spacecraft 3 and said object or area 25, as well as to the speed of the particles to be stopped.

The controller checks that the spacecraft 3 is in the desired direction and speed and, upon any detected and identified deviation from the pre-programmed direction and speed, rocket engines 7 are activated to stabilize and direct the spacecraft in the desired direction and speed. When the spacecraft 3 is in a designated location for distribution of substances 27, from at least one container 9, the computer unit activates, in this example, gas crane 13, not shown, and creates an overpressure that squeezes out said substances 27 through at least one nozzle 17 opened to a specified level and continuously spreads a certain amount of substances 27 in the desired direction.

A Control Center 1 on Earth continuously collects information from all spacecrafts 3 and cargo ships 23 included in the operation regarding, for example, location in the coordinate system, speed, amount of substance 27 and other supplies, fuel level and respective spacecrafts exact status at each moment as well as tasks performed and planned new ones. Control center 1 also monitor a variety of censors 31 located in space as well as placed on the object or area 25 to be protected. Furthermore, a radar unit 5 is scanning of the cloud and the amount and location of each scattered substance are transmitted. The information is used to determine the effect of work performed and to determine new actions. Based on established effect and new specific measured values, weather forecasts are then calculated for the time period with known effect from the Sun barrier 29. If necessary, the said Control Center 1 can oversteer the computer units of all spacecrafts 3 and transmit new instructions that each craft will then perform. The aim of the invention is to reduce damage caused by particles from the Sun, for example that a slightly lower temperature in water, air and soil will result in fewer natural disasters.

The spacecraft 3 is capable of automatic flying and navigating and in at least one embodiment equipped with radar unit 5 that is made to laterally scan over the existing Sun barrier 29 and at the same time issuing radar waves of a suitable wavelength. And in this example provided at the front part of the spacecraft 3, and which is rotatable and hinged in the end of a movable arm and the movements of which are controlled by means of electric circuits. The sensor is arranged for sensing density, size, and geographical density of Sun barrier 29 and, which in the illustrated embodiment is a screen of a Doppler radar unit 5. This contains both a transmitter and a receiver for suitable radar wavelengths. Received echo signals are delivered to a control unit placed inside the spacecraft 3 for performing an evaluation. Furthermore, a sensor, not shown, is provided for determining the position and the angular position of the radar screen in relation to the spacecraft 3. The signals from the position sensor are also supplied to the control unit. Sensors of different kinds for determining the substance 29 characteristics can be used, which have in particular been developed for localizing and to determine the character and distribution of clouds to calculate weather forecasts. And radar systems for identification of asteroids and comets near Earth, and also camera systems with high resolution in different wavelengths.

The received echo signals are transmitted to the computer unit 53 and its control unit. At the same time the signals of the position sensor are provided to the control unit, which correlates measured echo signals with different points on the Sun barrier 29 by evaluating both the signals from the position sensor and received position signals as to the absolute position of the spacecraft 3. The echo signals are evaluated and in particular for each point of the scanned Sun barrier 29 the depth and density of substances 27 and the size and form of the Sun barrier 29 are determined in a coordinate system where the horizontal direction refers to the part of the Sun barrier 29 closest to the Sun. And the said direction is used to determine the position of the scanned shape in relation to said object or area 25. Here different substances 27 and densities in all different directions as viewed from each considered point are determined as to their horizontal and vertical positions, their shape, etc. The determined data are stored and then evaluated for determining suitable spreading locations of substances 27. Then as input parameters the desired density of the Sun barrier 28 is used, which for example can be indicated as the number of kilos per hour spread from each specific point in space.

Furthermore, data in regard of already spread substances 27 are used in the determination of suitable amount to spread. The determined new spreading locations are stored. At the same time the control unit controls the nozzle 17, so that the container 9 and spreading device, in this example, a gas taps 13 is activated, and the signals from a position sensor are supplied to the control unit. And at the same time as controlling the degree of opening of the nozzle 17. Here is also a sensor, not shown, for determining the position for the device opening of the nozzle 17. The signals from the position sensor are in the same way as above supplied to the control unit. In order not to freeze substances in the container 9 and or to create steam from liquid, for example from liquid gas or water, a heating element, here called a heating means 11, not shown, can be activated. Here is also a sensor, not shown, and the signals from the activating and temperature sensors are supplied to the control unit. In the case where smoke is used to create the Sun barrier 29, a combustion chamber 21, not shown, with fire-means is connected to the container 9. Here is also a sensor, not shown, and the signals from the activating and position sensors are supplied to the control unit. When laser beams are used to create a Sun barrier 29, fine trimming of direction occurs with the help of electric motors, and also firing and supplying of the necessary substances is done with the help of electric motors, in this way known from military designs. Here is also a sensor, not shown, and the signals from the activating of different motors and their sensors are supplied to the control unit, as from all other movable or activable organs and other sensors on the spacecraft 3. Referring to FIG. 3. A block diagram of the electronic circuits of the spacecraft 3 in system 200 is illustrated. A central control unit 201 in the shape of a processor or a multitude of processors working in parallel receives signals from the location sensor, here a GPS antenna 55, from the radar unit 5 and from the position sensors 203, 205, 207, 209, 211, 213 and 215 for the various organs associated with the positions of 5, 7, 11, 13, 17, 19, and 21 respectively. The control unit 201 works according to a control rule, which can be divided in a number of processes or program routines working in parallel, which naturally can receive and transmit information to each other. A program routine 217 processes the GPS-signals and determines at each instant the exact absolute geographic location of the spacecraft 3 and its absolute direction of movement and speed, see also more detailed description in the description. All censors and organs are electrically operated and connected to a battery and connected to a computer device

Processes, 219, 221, 223, 225, 227, 229, 231 process the signals from the position sensors 203, 205, 207, 209, 211, 213, 215 respectively and determines based thereon the instantaneously true values of the position of the respective assembly in the relation to the spacecraft 3 and if the respective means are activated or inactivated in relation to a specific task in the spacecraft 3, i.e. the position in the height direction and horizontally and the angular position of the radar unit 5. The positions of the spacecraft in regard to exact direction and is a complement and safety equipment to GPS 55 and can consist of a camera and image analysis of where the Sun and Earth are in relation to the Spacecraft 3. And the positions of the rocket engine 7 in relation to the spacecraft 3, the positions of the censors for temperature and air pressure in the container 9 and the heating means 11 to prevent freezing or evaporate liquid, the position of the spreader means in the container 9, in this example gas crane 13, and if smoke is used as said substance 27 the positions of the censors for temperature and air pressure in the combustion chamber 21 and the position for the heating means, the positions of the censors for nozzle 17 regarding the degree of opening. And the positions of the censors for directions of the laser canon 19, and here it is assumed that other necessary supplies and equipment also function according to the selected type of laser cannon, even if it is not described in more detail.

Then the positions are absolutely determined by accessing information as to the absolute location/position of the spacecraft 3 from the module 217. A process 233 processes the signals from the radar unit 5 for determining depth, size, and density, etc. of Sun barrier 29, and correlates the calculated data with the correct absolute geographic position by receiving current position data from the module 217. The calculated data values are stored in a mass storage 235. The stored data of the Sun barrier 29 are then further evaluated in a module 237, which in an optimal way determines size and locations of different densities in the cloud. For the determination the location determining module 237 also has access to the location of already spread substances 9 locations, which are stored in a memory 239. After having determined new spreading locations, the location thereof are stored in the memory 239.

Control processes 241, 243, 245, 247, 249, 251 and 253 control the different movable parts 5, 7, 11, 13, 17, 19, and 21 respectively of the spacecraft 3, i.e., the movement of the radar screen 5, the movements of the rocket engine 7 and energizing the start assemblies thereof and energizing of the heating means 11 and the movements of the gas crane 13. And the movement of the nozzle 17, the movements of the laser cannon 19 and energizing the fire assemblies thereof or, depending on the selected substance, energizing of the heating/fire means 21 in the combustion chamber. For this control they have access to the current position and magnitudes of their respective organ and for all organ except the radar screen 5 the determined location of new spread/ firing places.

The control modules 241, 243, 245, 247, 249, 251 and 253 transmit signals to driver circuits for the different components. The control module 241 thus transmits signals to driver circuits 255 for operating the radar arm. The control module 243 transmits signals to driver circuits 257 for operating the rocket engine direction and to driver circuits 259 for start and operating the rocket assembly. The control module 245 transmits signals to driver circuits 261 for operating the heating means. The control module 247 transmits signals to driver circuits 263 for operation the gas crane. The control module 249 transmits signals to driver circuits 265 for operation the heating means in the combustion chamber. The control module 251 transmits signals to driver circuits 267 for operating the nozzle assembly. The control module 253 transmits signals to driver circuits 269 for operating the direction means for laser cannon and to driver circuits 271 for operation the fire mechanism. Further it is marked in the memory 239 after finishing an operation in the respective location.

Signals in regard of the current position of the spacecraft and data from all censors on the spacecraft can be transmitted to a control Center 1 located on Earth and the information is transmitted via the transmitter / receiver 41 placed on the spacecraft and the transmitter / receiver 39 placed on the Control Center 1. Transmitted information may, for example, consist of work performed and planed new measures and status of substances and supplies, and data collected from the continuous radar scan 5. Control Center 1 collect information from censors on the spacecraft and from censors 31 placed on the protected object or area and from censors 33 placed on satellites, and based on the information collected, the actual effect of the shading is calculated and determined. And can be described as a percentage decrease in solar radiation for a specific object or area, and with knowledge of future spreading of substances and how it will affect the said effect, so can the decrease in solar radiation for a certain period of time be determined. The new value for solar radiation is then used to calculate weather forecasts and deciding whether to change the obscuring effect. Control Center 1 can override stored commands in the spacecrafts computer unit and, for example, increasing or decreasing the spread rate or changing speed and direction of movement for spacecrafts.

Referring to FIG: 4A, a principle drawing is shown according to an exemplary embodiment of creation of a Sun barrier 406 in an inner orbit 43 around the Sun in order to protect an object or area 409 traveling in an outer orbit 45. And 59 shows a schematic view of funnel-shaped travel path for particles having a specific velocity and living the Sun in this moment. In Control Center 411 calculates where when and how much to spread of at least one type of substances 407 and sends information about new decisions to one or more spacecrafts 401 capable of automatic flying and navigating. Control center 411 monitors the status in real time of all spacecrafts involved in the work via censors, and whose signals are sent to Control center 411 via the spacecraft’s 401 network interface 426 that comprise a transmitter unit 41. Furthermore, Control center 411 collects continuous information from censors 31 placed on satellites that measure the amount/number of particles passing before and after Sun barrier 406 as well as censors on the protected object or area 409. Furthermore, control center 411 collects information from spacecraft’s 401 equipped with radar units 404 that scan the Sun barrier 406 and make a map of the size, distribution, and density of the Sun barrier 406, in the form of a cloud and, for example, whether this will lead to some of said object or area 409 having more protection than others. The collected information from censors 31 is used to calculate whether the desired effect has been achieved, or if more or less substances 407 should be spread in one or more areas of the Sun barrier 406 by one or more spacecrafts 401. Collected information and new planned measures, such as reduced or increased dispersion of substances 407, are also used to calculate, for example, percentage reduced solar radiation, which is then included in calculations for weather forecasts.

Referring to FIG. 4A and 4B, a Sun barrier characteristic and mapping and spreading system 400 is shown according to an exemplary embodiment. System 400 comprises a determined location for the protected object or area 409 and includes an automatic flying spacecraft 401 and a spreading device 402 and may be integrated into spacecraft 401. Spacecraft 401 includes GPS receiver 403 and a Sun barrier sensor, shown as radar unit 404, for example a pulse-doppler radar. The radar unit comprises sensors for detecting angles for the radar screens direction in a coordinate system and the distance and angle to the different parts of the sun barrier. The radar unit 404 comprising in at least one embodiment a camera unit 408 taking pictures, and advantageously in different wavelengths of the Sun barrier 406. GPS receiver 403 receives signals from GPS satellites 405 and is configured to provide a feedback signal used to track the location of spacecraft 401. Radar unit 404 utilizes radar to determine and extrinsic characteristics of Sun barrier 406. Exemplary intrinsic Sun barrier characteristics may include a composition of the Sun barrier, a water property of the Sun barrier (e.g., how much water is contained in a cloud and the volume and density), a presence of gas in the Sun barrier material, the density, material porosity, and any other intrinsic characteristics Sun barrier 406 may have. Exemplary extrinsic Sun barrier characteristics may include the presence of smoke, the depth of Sun barrier, any other spacecrafts in or near the Sun barrier 406, and any other extrinsic characteristic of Sun barrier 406. Spreading device 402 comprises a container 410 containing the substances 407 which are to constitute the said Sun barrier 406. The substances 407 is spread around the spacecraft 401 or in a specific direction, for example against the Sun in order to make the Sun barrier 406. That means that the spreading device 402 is adjustable such that the substances 407 can be spread at different directions within Sun barrier 406. Spreading device 402 is controllable such that substances can be placed and form various densities (e.g., at a designated amount of substances 407 per area). System 400 is generally configured to detect Sun barrier characteristics through radar unit 404 and adjust spreading device 402 based on detected Sun barrier characteristics. Further, system 400 is configured to generate a map of Sun barrier 406 by pairing location data from GPS receiver 403 with Sun barrier characteristic data from radar unit 404. The map created by system 400 is a collection of data points coupled to location information, that when processed, may be reproduced into a visual representation of the map (e.g., for viewing by an operator through a display) or a set of data and location points for further processing by a system controller (e.g., to properly instruct substances or laser beam placement). The collected map data points may be stored in an R-tree data structure, an array data structure, or another suitable data structure. The map may be a three-dimensional map. The details of the operation of system 400 are described below.

In one embodiment, radar unit 404 is a Doppler Sun barrier-penetrating radar unit. Radar unit 404 emits in this example electromagnetic radio waves into Sun barrier 406. As the waves travel through Sun barrier 406, portions of the waves are reflected back at different strengths depending on the composition of Sun barrier 406 and the presence and depths of objects within Sun barrier 406. Radar unit 404 is capable of detecting the presence and depth of, for example, smoke, coal or ash, and water and any other objects or matter within Sun barrier 406 based on reflected radio wave signatures (i.e., extrinsic characteristics in order to determine if it can protect an object or area 409 having determined coordinates and traveling in a determined location in a coordinate system,). The utilization of high-frequency radio waves enables radar unit 404 to scan even thick clouds near the spacecraft 401. And, advantageously at a high resolution such that it can detect Sun barrier characteristics (e.g., Sun barrier composition and density), the presence of water, the density of water, the amount of water, the presence and type of minerals present in Sun barrier 406, the presence and amount of ash, smoke, coal or chemicals in Sun barrier 406, and other Sun barrier characteristics (i.e., intrinsic characteristics). When camera 408 is included in the scan of the Sun barrier 406 both size and amount of substances 407 can be calculated if the wavelength is adapted to the content. Advantageous several units are used, and the size of the cloud can also be laser measured and the size and extent of the cloud is determined in the coordinate system.

Radar unit 404 may transmit unmodulated continuous -wave signals that are used to create a plan-view hologram of Sun barrier 406. In an alternate configuration, reflection is used to transmit acoustic waves through Sun barrier 406, and reflected acoustic waves are analyzed to determine the composition of Sun barrier 406 and the location of objects within Sun barrier 406. Radar unit 404 provides feedback signals that include data pertaining to detected Sun barrier characteristics to controller 420 (as shown in FIG. 4B), where the data is processed into a three-dimensional map of Sun barrier 406. The collected and calculated information is also sent in real time to the Control Center 411 to be included in the calculation of weather forecasts for the protected object or area 409.

Referring to FIG. 4B, a block diagram of controller 420 is shown. Controller 420 includes processing circuit 421. Processing circuit 421 includes processor 422 and memory 423. Processing circuit 421 communicates with GPS receiver 403, radar unit 404, spreading device 402, user input 424, user output 425, and network interface 426. Controller 420 is powered by power supply 427. Memory 423 stores necessary programming modules that when executed by processor 422, control the operation of spreading device 402 and the creation of the three-dimensional map of Sun barrier 406 based on settings, parameters, and feedback signals received through input 424, GPS receiver 403, and radar unit 404. User input 424 is configured to provide an interface for a user to input desired operational parameters for system 400 (e.g., type of substances being placed in the container 410, desired Sun barrier characteristics for spreading, density of spreading, etc.). User input 424 includes a series of knobs, wheels, multi -position switches, a keyboard, a mouse, or any combination thereof, and connected to a computer device in order to be taken over in real time by commands from the control center located on Earth. User output 425 includes a display. User output 425 optionally includes audio output (e.g., for emitting beeps and tones) and/or indicator lights (e.g., LEDs for indicating system 400 statuses and alerts). It is contemplated that user input 424 and user output 425 are combined into a touchscreen display such that a user of system 400 can program desired settings and parameters through interaction with a graphical user interface presented on the display. Network interface 426 is configured to communicate with an external server or an external computing device, here called Control Center 411 and located on Earth. Power supply 427 provides power to controller 420. Power supply 427 may provide power to all components of system 400 (e.g., GPS receiver 403, radar unit 404, etc.). Power supply 427 may receive power from any suitable source (e.g., a rechargeable battery, a generator onboard spacecraft 401, solar panels or a portable nuclear reactor etc.).

Controller 420 is configured to process feedback signals from GPS receiver 403 and radar unit 404 based on provided operating parameters. As spacecraft 401 moves along the path on its orbit around the Sun and create the Sun barrier 406, and controller 420 receives feedback signals from radar unit 404 that indicates detected Sun barrier characteristics and GPS receiver 403 that indicate spacecraft 401's location. Controller 420 processes these feedback signals into a detailed three-dimensional map of Sun barrier 406. The three- dimensional map includes location specific information pertaining to the composition of Sun barrier 406 (e.g., chemical composition, moisture amount, density, material presence, etc.), the presence of objects (e.g., smoke, coal, or ash etc.), and other information pertaining to Sun barrier 406 up to a specified depth or straight through the Sun barrier 406. The depth parameter of the three-dimensional map (e.g., the shape of the whole Sun barrier 406, for example in the form of a cloud and the size and density of all parts of the cloud etc.) And may be a user provided parameter. Controller 420 is configured to analyze feedback signals from radar unit 404 to locate and identify objects in the Sun barrier 406 (e.g., smoke, coal or ash, Sun barrier water etc.). Detected objects are identified by their radar signatures. For example, radar waves reflected off water will have a different signature than radar waves reflected off smoke, coal, or ash.

Controller 420 automatically determines the identity of different substances 407 in Sun barrier 406. Alternatively, substances 407 are manually identified and updated on the map through user input. For example, substances 407 that cannot be automatically identified are marked as unknown on the map. The user then manually identifies the unknown objects, and the user can identify the object on the map and the object's identity can be stored. Alternatively, the user may choose to have the object remain unidentified. As spacecraft 401 moves along the path on its orbit around the Sun and create the Sun barrier 406, controller 420 instructs spreading device 402 to spread substances 406. Spreading device 402 is capable of spreading substances at varying direction and densities, by for example, varying the degree of opening of a nozzle, by sending a signal to an electric motor which regulates the opening of the nozzle. Based on user provided parameters and detected Sun barrier conditions, controller 420 instructs spreading device 402 to spread a specific amount of substances at specific locations and at specific time or time period. For example, controller 420 may instruct such that substances 407 are placed in desirable locations and are not placed in undesirable direction, speed or locations (e.g., in a location where the particles that are stopped would miss the protected object or area 409 anyway etc.). In one embodiment the spreading device 402 comprises a laser canon and where motors direct the canon towards the Sun. And where control organs and feed organs can be designed according to the equipment used for this type of canon on aircraft carriers.

Upon the successful placement of substance 407 by spreading device 402, controller updates the map of Sun barrier 406 to indicate the placement of the substances 407 (e.g., marks the map with an indication of the substances 407 placement). The created map may be exported to an external computing device via network interface 426, stored in memory 423, or stored on removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.). The user can then reference the created map after Sun barrier 406 has been mapped and/or after substances 407 have been delivered. By determining the size of the cloud and its density over the entire cloud and exact coordinates, speed and direction of movement so can it also be calculated which areas on the object or area 409 certain parts of the cloud will obscure during a certain time or time interval. And with knowledge of how each type of substances 407 will thin out and how the cooling effect will gradually decrease so can the need for supply of more substances be calculated. To measure particle current passing the Sun barrier 406, censors are placed on satellites between the Sun barrier 406 and the said objects or area 409 and the information is sent to and processed by Control Center 411. The information collected is also used to calculate weather forecasts and can be stated, for example, as a percentage reduction in solar radiation for each specific area. Where the information is included in regular weather calculations.

Referring to FIG. 5, a method of operating a system configured to spread substances 407 from an orbit around the Sun and create a map of an area of space based on detected Sun barrier 406 characteristics (e.g., system 400) is shown according to an exemplary embodiment. The system includes a spacecraft 401 configured and equipped with means to map Sun barrier characteristics and substances. The user programs operating parameters into the system (step 501). The operating parameters include spreading parameters. The spreading parameters include any of the type of substances being spread, desired substances placement, amount, characteristics etc., The user input includes a series of knobs, wheels, multi -position switches, a keyboard, a mouse, a touchscreen display, or any combination thereof. A user can program spreading parameters on an external computing device (e.g., a computer, a smartphone, a PDA, a tablet, etc.), and upload the spreading parameters to the spacecraft's controller. The upload may occur via a network connection between the spacecraft's controller and the external computing device The spacecraft 401 may be autonomous and capable of navigating to an orbit around the Sun and a predefined spreading pattern based on location feedback from the on-board GPS sensor and computerized control of the spacecraft's 401 throttles and rocket engines and steering mechanisms. In such an arrangement, the user provided parameters include a detailed spreading pattern over a designated area in space, such as a predefined location and size on one or more Sun barriers 406. The user provides the spreading pattern by inputting the coordinates for the path the spacecraft 401 should travel on its orbit around Sun. Comprising the direction of travel and speed, and at what time or time interval to start and stop spreading, and on which coordinate or coordinates to open the nozzle by activating Spreading device 402 to create the Sun barrier 406.

Further referring to FIG. 5, the controller then navigates the spacecraft through the spreading pattern (step 502). The Sun barrier and status of the spacecraft is displayed to the user in a Control Center such that the user can override command stored in the spacecrafts computer unit and operate the spacecraft. And the user can instructs the spacecraft to begin the spreading and mapping process. As the spacecraft follows the spreading pattern, the spacecraft is configured to detect Sun barrier characteristics and chart the detected Sun barrier characteristics on a map (step 503). The spacecraft includes a Sun barrier -penetrating radar unit. The radar unit detects the presence and depth of, for example smoke, coal, ash or water, and any other objects within the Sun barrier or on the surface of the Sun barrier (i.e., extrinsic Sun barrier characteristics). The radar unit utilizes reflected wave data to create a series of high resolution scans of the Sun barrier (e.g., depth slices, time slices, three-dimensional image blocks, etc.), and to detect changes in Sun barrier characteristics (e.g., composition, and density), the presence of water, the depth of the water, the amount of water, the presence and type of minerals, the presence and amount of smoke, and other characteristics (i.e., intrinsic Sun barrier characteristics). As the spacecraft navigates along the orbit and create the Sun barrier, the spacecraft spread substances according to the programmed parameters (step 504). The controller of the spacecraft sends instructions to a spreading device of the spacecraft. The controller instructs the spreading device to spread substances at designated locations. The designated locations are determined based on at least one of feedback received from the radar unit and the user provided spreading parameters. The user may indicate that substances are to be placed along the designated spreading pattern regardless of detected Sun barrier characteristics.

Alternatively, a user indicates that substances are to be placed along a designated spreading pattern only if satisfactory Sun barrier characteristics are detected. For example, a user may indicate that the controller is to instruct substances placement in Sun barrier containing a threshold level of density, a threshold level of water in the form of ice crystals, the direction of travel and velocity of the substance in relation to the desired one, etc. In yet another alternative embodiment, a user indicates that substances are to be placed along a designated spreading pattern unless unsatisfactory Sun barrier characteristics are detected. The controller further instructs the spreading mechanism to place the substances according to a specified direction. The direction is set by the user as part of the provided parameters (provided in step 501). Alternatively, the controller may automatically adjust direction based on the type of substances being spread and/or the detected characteristics of the Sun barrier. The direction may be adjusted to avoid the substances from travel in the wrong direction or speed, or to place substances in undesirable areas of the Sun barrier, or to avoid lump formation of smoke, coal or ash, as an obstacle cannot become more than impenetrable, and all substances over it has no effect. All spreading is charted on the map, (e.g., the controller places an indication on the map pertaining to the location of the substances). After placement of the substances is complete, a signal indicates to the controller of the spacecraft that the spreading pattern is finished (step 505). And the spacecraft indicates to the Control Center 411 that the pattern is complete. The user in the control center is then alerted to the presence of any abnormalities or unidentified substances or objects detected within the Sun barrier (step 506), as this may affect efficiency and weather forecasts and the like. The controller of the spacecraft is configured to analyze and identify objects through the surface of the Sun barrier based on the objects' radar signatures. In some situations, the controller may not be able to determine an object's identity. Accordingly, the controller alerts the user of the unidentified object's presence through a user output mechanism (e.g., a display) of the Control Center. The user can then input the identity of the object such that the object is marked and noted on the map through a user input mechanism of the spacecraft (step 507). Alternatively, the user can ignore the alert and the object will remain on the map as unidentified or delete the unidentified object (e.g.,). If no unidentified objects are detected, (step 507) is skipped. After any unidentified objects are identified, the map may be saved and exported (step 508). The created map indicating the detected Sun barrier characteristics and substances placement is stored in memory associated with the controller of the system. The created map may be exported to an external computing device via a network interface or stored on removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.). The user can then access the map on an external computing device. For example, the map may be beneficial for predicting weather forecasts, and for identifying areas of Sun barrier that require additional substances. And for identifying areas of Sun barrier containing an abnormal amount of undesirable characteristics that need to be fixed (e.g., clouds of smoke, coal or ash that need more substances), and for use in future spreading operations.

Referring to FIG. 6A, a stand-alone mapping system 600 is shown according to an exemplary embodiment. System 600 includes an object or area orbiting the Sun in an outer orbit 45, for example the Earth, Moon, Mars, or a spacecraft and at least one mapping unit 602 is placed on a spacecraft 601. In the example shown so constitute the mapping unit 602 an attachment to spacecraft 601 (e.g., configured to fit into a spacecraft, etc.). Although mapping unit 602 is shown as an attachment to spacecraft 601, it should be understood that a mapping unit 602 may be fully integrated into a spacecraft or placed on any flying object in the solar system, as long as the radar can be aimed at the Sun barrier, here shown in orbit 43 and the protected object or area, in this example the whole Earth is shown in orbit 45. Mapping unit 602 includes GPS receiver 603 and a Sun barrier sensor, shown as radar unit 604 coupled to the housing of mapping unit 602. GPS receiver 603 receives signals from GPS satellites 605 and is configured to provide a feedback signal used to track the location of spacecraft mapping unit 602. In alternative embodiments, other location sensors can be employed instead of, or in conjunction with, GPS. For instance, mapping unit 602 can include inertial navigation equipment, which is initialized with respect to a space reference site, and which may be updated during the mapping/spreading session. In another embodiment, mapping unit 602 can interact with a local metrology system, e.g., RF or, optical navigation by using stars and planets. Radar unit 604 utilizes radar to determine intrinsic and extrinsic characteristics of Sun barrier 606. Radar unit 604 is similar to radar unit 404 of system 400. Accordingly, radar unit 604 is a doppler radar or other non-insertion radar units and emits radar waves into Sun barrier 606. As the waves travel through Sun barrier 606, portions of the waves reflect back at different strengths depending on the composition of Sun barrier 606 and the presence and depths of objects within Sun barrier 606. Radar unit 604 is capable of detecting the presence and depth of substances, objects and characteristics of Sun barrier 606.

Radar unit 604 may transmit unmodulated continuous -wave signals that are used to create a plan-view hologram of Sun barrier 606. In another alternate configuration, reflection is used to transmit acoustic waves through Sun barrier 606, and reflected acoustic waves are analyzed to determine the composition of Sun barrier 606 and the location of objects within Sun barrier 606. Radar unit 603 provides feedback signals that include data pertaining to the detected Sun barrier characteristics to controller 610 (shown in FIG. 6B). Mapping unit 602 is generally configured to detect characteristics of Sun barrier 606 through radar unit 604 and generate a map of Sun barrier 606 by pairing location data from GPS receiver 603 with Sun barrier characteristic data from radar unit 604. The map created by system 600 is a collection of data points coupled to location information, that when processed, may be reproduced into a visual representation of the map (e.g., for viewing by an operator through a display) or a set of data and location points for use by another system (e.g., to determine proper substances or substances placement). The collected map data points may be stored in an R-tree data structure, an array data structure, or another suitable data structure. The map may be a three-dimensional map.

Referring to FIG. 6B, a block diagram of controller 610 is shown in accordance with an exemplary embodiment. Controller 610 controls the operation of mapping unit 602. Controller 610 includes processing circuit 611. Processing circuit 611 includes processor 612 and memory 613. Processing circuit 611 communicates with GPS receiver 603, radar unit 604, user input 614, user output 615, and network interface 616. Controller 610 is powered by power supply 617. Memory 613 stores necessary programming modules that when executed by processor 612, control the operation of mapping unit 602 and the creation of a three-dimensional map of Sun barrier 606 based on settings, parameters, and feedback received through user input 614, GPS receiver 603, and radar unit 604. User input 614 is configured to provide an interface for a user to input desired mapping parameters for system 600 (e.g., size of area to be mapped, type of Sun barrier to be mapped, sensitivity level of radar unit 604, etc.). User input 614 includes a series of knobs, wheels, multi-position switches, a keyboard, a mouse, or any combination thereof. User output 615 includes a display. User output 615 optionally includes audio output (e.g., for emitting beeps and tones) and indicator lights (e.g., LEDs for indicating system 600 statuses and alerts).

It is contemplated that user input 614 and user output 615 are combined into a touchscreen display that displays an interactive graphical user interface such that a user of system 600 can program desired settings and parameters through interaction with the display. Network interface 616 is configured to communicate with an external server or an external computing device. Network interface includes at least one of an Ethernet interface and a wireless transceiver. An external computing device remote from controller 610 can provide an interface for a user to input desired mapping parameters for system 600 and to control system 600 (e.g., a computing device located in the Control Center on Earth). In this arrangement, the external computing device transmits user provided input to controller 610 through network interface 616 and receives system 600 output transmitted by network interface 616. Power supply 617 may receive power from any suitable source (e.g., a battery, a solar panel onboard spacecraft 601). Power supply 617 may provide operational power to all components of mapping unit 602, including GPS receiver 603, radar unit 604, user input 614, and user output 615.

As in system 200 and 400, controller 610 of system 600 is configured to process feedback signals from GPS receiver 603 and radar unit 604 into a detailed map of Sun barrier 606. As the object or area and in this example a spacecraft 601 moves in an orbit around the Sun and scan the Sun barrier 606. Controller 610 receives feedback signals from radar unit 604 that indicate characteristics of Sun barrier 606 and GPS receiver 603 that indicate the location of the object or area, and in this example, a spacecraft 601. Controller 610 is configured to process these feedback signals into a detailed three-dimensional map of Sun barrier 606. The three-dimensional map includes location specific information pertaining to the composition of Sun barrier 606 (e.g., chemical composition, moisture amount, density, smoke presence, etc.), the presence of objects and other information pertaining to Sun barrier 606 up to at least a specified depth beneath the surface of Sun barrier 606.

The depth parameter of the three-dimensional map may be a user provided parameter. Controller 610 is configured to analyze feedback signals from radar unit 604 to locate and identify substances or objects on or underneath the surface of Sun barrier 606 (e.g., smoke, coal or ash, or water in any form, etc.). Detected substances and objects are identified by radar signatures. Controller 610 is configured to automatically determine the identity of objects beneath the surface of Sun barrier 606. Alternatively, objects are manually identified and updated on the map through user interaction. For example, controller 610 may not be able to ascertain the identity of a detected object or characteristic. Accordingly, the user may be alerted of an unidentified object's location such that the user can manually identify the object, clear the object from the map, or leave the object as unidentified on the map. The created map can be exported to an external computing device via network interface 616 or be stored on removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.). The user can then reference the created map for assistance during future Sun barrier processing operations (e.g., spreading, weather forecasts, etc.).

Referring to FIG. 6C, a method 620 of operating a stand-alone Sun barrier mapping system (e.g., system 600) is shown. The user programs operating parameters into the system (step 621). The operating parameters may include a desired map depth (e.g., a designated number of feet or meters through the surface of the Sun barrier) and a map resolution indication. In certain situations, it is desirable to have a high-resolution map created. For example, a high -resolution map is desirable if the map will be used in a precision spreading operation that requires precise location information for detected intrinsic and extrinsic Sun barrier characteristics. If a high resolution is desired, the radar unit of the system utilizes high- frequency radio waves during the mapping process. In other situations, it may be desirable to have a low- resolution map created (e.g., a map indicating the presence and location of large objects trough the surface of the Sun barrier, but not other Sun barrier characteristics such as Sun barrier composition). For example, a low-resolution map may be desirable if the map will only be needed to identify large accumulations of dispersed substances. If a low resolution is desired, the radar unit of the system utilizes low -frequency radio waves during the mapping process. The spacecraft is configured to work autonomous and is capable of navigating a predefined mapping pattern based on location feedback from the on-board GPS sensor and computerized control of the spacecraft's throttle and steering mechanisms. The operating parameters may include a detailed mapping pattern over a designated area of space, such as a predefined part of a Sun barrier. The user in the Control Center may provide the mapping pattern by drawing a Sun barrier overlay on a screen representing the area of space to be mapped. Alternatively, the user may select a plot of space from a NASA mapping service etc.), and the controller of the system automatically computes a suggested spacecraft for complete mapping of the plot of space. The suggested part of a Sun barrier is presented to the user for verification. The user can then accept, reject, or modify the suggested Sun barrier. If the user accepts or modifies the suggested Sun barrier, the system is ready to begin autonomous operation of the spacecraft by tracking the location of the spacecraft through the GPS receiver and making steering and throttle adjustments such that the spacecraft remains on the determined location in relation to the Sun barrier.

The user in a control center instructs the spacecraft to begin navigating the spacecraft in the part of space to be mapped (e.g., by following the suggested Sun barrier) (step 622). As the spacecraft follows the mapping pattern, the spacecraft is configured to detect Sun barrier characteristics and chart the detected Sun barrier characteristics on a map (step 623). The spacecraft includes a Sun barrier-penetrating radar unit. The radar unit is a doppler radar unit and preferably also a camera unit. The radar unit detects the presence and depth of smoke, coal or ash, water, and any other objects within the Sun barrier. The radar unit captures a series of high-resolution scans of the Sun barrier (e.g., depth slices, time slices, three-dimensional image blocks, etc.), and to detect Sun barrier characteristics (e.g., composition and density), the presence of water, the amount of water, the presence and type of minerals, the presence and amount of matter and other Sun barrier characteristics.

In an alternate configuration, the radar unit transmits unmodulated continuous -wave signals that are used to create a plan-view hologram of the Sun barrier. In another alternate configuration, reflection is used to transmit acoustic waves through Sun barrier, and reflected acoustic waves are analyzed to determine the composition of Sun barrier and the location of objects within Sun barrier. The radar unit provides feedback signals data relating to captured radar scans to the controller of the spacecraft. The controller combines the radar scan information with information from the GPS receiver to create a dimensional map of the area traversed by the spacecraft. The map created by the system is a collection of data points coupled to location information, that when processed, may be reproduced into a visual representation of the map (e.g., for viewing by an operator through a display) or a set of data and location points for use by a system controller in further processing (e.g., the controller of a system may process the map data to instruct placement of substances). The collected map data points may be stored in an R-tree data structure, an array data structure, or another suitable data structure. The map may be a three-dimensional map.

Further referring to FIG. 6C, the user in the Control Center can indicates to the spacecraft that the Sun barrier to be mapped has been mapped and stops the mapping process (step 624). Alternatively, the spacecraft indicates to the user in said Control Center that the pattern is complete. Upon completion, the user in the Control Center is alerted to the presence of any unidentified objects detected within the Sun barrier (step 625). The controller of the spacecraft is configured to analyze and identify objects through the surface of the Sun barrier based on the objects' radar signatures. The controller may not be able to determine every detected object's identity. Accordingly, the controller alerts the user of the spacecraft to any unidentified object's presence. The user can then input the identity of the object such that the substances or object is marked and noted on the map (step 626). Alternatively, the user can ignore the alert (i.e., the object remains on the map as an unidentified object) or deletes the unidentified object from the map. If no unidentified objects are detected, step 625 is skipped. After the unidentified objects are identified, ignored, or removed, the map is saved and exported (step 627). The created map indicating the detected Sun barrier characteristics is stored in memory associated with the controller of the system. The user may wish to save the map for later viewing and analysis. For example, the map may be beneficial for plotting future spreading operations and weather forecasts. The created map can be exported to an external computing device via a network interface or can be stored on removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.).

Referring to FIG. 7A, a stand-alone precision spreading apparatus in the form of an automatic flying spacecraft 700 is shown in accordance with an exemplary embodiment for protecting a location determined object or area, for example in a coordinate system. Spacecraft 700 includes GPS receiver 701 and spreading device 702. GPS receiver 701 receives signals from GPS satellites 703 and is configured to provide a feedback signal used to track the location of spacecraft 700. Spreading device 702 is configured to spread a specific amount of substances 705 on a specific location at a specific time or period collected from the controllers storage unit and time unit and create a Sun barrier 704, and in this example in the form of a cloud of substances 705. Spreading device 702 is adjustable such that substances can be directed at different directions. Spreading device 702 is controllable such that substances can be placed at various densities. Spacecraft 700 is generally configured to precisely spread substances 705 based on location data received from GPS receiver 701, provided spreading parameters, and Sun barrier characteristic data received from a provided map of Sun barrier 704. The provided map is a collection of data points coupled to location information, that when processed, may be reproduced into a visual representation of the map (e.g., for viewing by an operator through a display) or a set of data and location points for further processing (e.g., the map data may be processed to determine proper substances placement). The collected map data points may be stored in an R-tree data structure, an array data structure, or another suitable data structure. The map may be a three-dimensional map.

Referring to FIG. 7B, a block diagram of controller 710 is shown. Controller 710 generally controls the operation of spacecraft 700. Controller 710 includes processing circuit 711. Processing circuit 711 includes processor 712 and memory 713. Processing circuit 711 communicates with GPS receiver 701, spreading device 702, user input 714, output 715, and network interface 716. Controller 710 is powered by power supply 717. Memory 713 stores necessary programming modules that when executed by processor 712, control the operation of spacecraft 700, including the operation of spreading device 702, receiving user input, providing user output, communications over network interface 716, and updating any provided map data. User input 714 is configured to provide an interface for a user to input desired spreading parameters for spacecraft 700 (e.g., type of substances being spread, desired Sun barrier characteristics for spreading, density of spreading, spreading pattern, etc.).

User input 714 includes a series of knobs, wheels, multi-position switches, a keyboard, a mouse, or any combination thereof. User output 715 includes a display. User output 715 optionally includes audio output (e.g., for emitting beeps and tones) and/or indicator lights (e.g., LEDs for indicating spacecraft 700 statuses and alerts). It is contemplated that user input 714 and user output 715 are combined into a touchscreen display such that a user of spacecraft 700 can program desired settings and parameters through interaction with a graphical user interface presented on the display. Network interface 716 is configured to communicate with an external server or an external computing device. Network interface 716 includes at least one of an Ethernet interface and a wireless transceiver. Power supply 717 provides power to controller 710. Power supply 717 may provide power to all components of spacecraft 700 (e.g., GPS receiver 701, spreading device 702, etc.). Power supply 717 may receive power from any suitable source (e.g., a rechargeable battery, a non-rechargeable battery, a generator onboard spacecraft 700, a nuclear reactor, or solar panels that powers spacecraft 700, etc.).

Controller 710 instructs spreading device 702 to place substances in Sun barrier 704 based on processed feedback signals from GPS receiver 701 and provided spreading parameters. As spacecraft 700 moves along Sun barrier 704, controller process’s location feedback signals from GPS receiver 701 to track the location of spacecraft 700. Controller 710 compares the location of spacecraft 700 to provided map data. The map data pertains to a three-dimensional map of Sun barrier 704 including location specific information pertaining to the composition of Sun barrier 704, (e.g., chemical composition, moisture amount, density, humus presence, etc.), the presence of substances and objects (e.g., buried smoke, coal or ash, etc.), and other information pertaining to Sun barrier 704 thought or up to a certain depth beneath the surface of Sun barrier 706. The map data may have been initially created through the use of a Sun barrier mapping system (e.g., system 200 or 400). The map is received into memory 713 from an external computing device or server through network interface 716 or from removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.) provided by the user. As spacecraft 700 moves along Sun barrier 704, controller 710 instructs spreading device 702 to spread substances 705 to create Sun barrier 704 at specific locations based on provided spreading parameters and Sun barrier conditions contained within map data. For example, controller 710 is configured to adjust spreading device 702 such that substances are placed in desirable locations for maximal shadow effect on the protected object or area. Upon the successful spreading of a substances by spreading device 702, controller 710 updates the map of Sun barrier 704 to indicate the placement of the substances 705. The modified map may be saved and exported to an external computing device via network interface 716 or stored on removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.). Referring to FIG. 7C, a method 720 of precision spreading through a spreading system (e.g., spacecraft 700) based on provided spreading parameters and map data. The user of the system provides map data pertaining to an area of the Sun barrier to spread Substances (step 721). The map data relates to a three- dimensional map of an area of Sun barrier to spread Substances and includes location specific information pertaining to the composition of the Sun barrier, (e.g., chemical composition, moisture composition, density, presence of different substances, etc.), the presence of objects, and any other information pertaining to Sun barrier. The map includes this information through or up to a specified depth beneath the surface of the Sun barrier. The map data is a collection of data points coupled to location information, that when processed, may be reproduced into a visual representation of the map (e.g., for viewing by an operator through a display) or further processed by a controller of the system (e.g., to determine proper substances placement). The collected map data points may be stored in an R-tree data structure, an array data structure, or another suitable data structure. The map may be a three-dimensional map. The map data may have been created through the use of a Sun barrier mapping system (e.g., system 600). The map data is provided to a controller of the system from an external computing device or server through network interface of the controller or with a removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.).

The user programs spreading parameters to the precision spreading spacecraft (step 722). The spreading parameters include any of the type of substances being spread, desired placement, characteristics (e.g., density, future processing strategy (e.g., spreading strategy, number of spacecrafts, capacity, etc.), and any other desired spreading parameter. The spreading parameters may include threshold levels of detected Sun barrier characteristics to avoid spreading substances. For example, a user may indicate that substances are not to be placed in Sun barrier containing a threshold percentage or density of smoke, coal or ash. Further, the spreading parameters may include threshold levels of detected Sun barrier characteristics for substances placement. For example, a user may indicate that substances are to be placed in Sun barrier containing a threshold level of smoke. The spreading parameters may include a subset of the provided map data indicating that only a portion of the area is to be used on specific coordinates. The user provides the spreading parameters to the system through a user input.

The user input includes a series of knobs, wheels, multi-position switches, a keyboard, a mouse, a touchscreen display, or any combination thereof. Alternatively, a user programs spreading parameters on an external computing device (e.g., a computer, a smartphone, a PDA, a tablet, etc.) and uploads the spreading parameters to the controller. The upload may occur via an ad-hoc network connection between the controller and the external computing device, via removable storage media (e.g., SD Card, USB flash drive, etc.), or via downloading the parameters from a host server. Further, the system may automatically determine spreading parameters based on a user selection of a spreading parameter template (e.g., a cloud or a line) and a designated an area of space to be a Sun barrier. The template includes preset spreading parameters (e.g., type of substances, placement, density, desired Sun barrier composition, placement strategy, etc.). The user can modify the preset spreading parameters of the template. The controller of the system then processes a spreading pattern (step 723). The spreading pattern is created through processing of the provided spreading parameters and provided map data. The controller of the system determines where substances should be placed according to the spreading parameters, (e.g., in a cloud, in a line, in areas having tin or no layers of substances, etc.). The spreading pattern maximizes the effect of the substances, for example laser beams with the designated pattern on the area to be one or more Sun barrier. The controller determines the specific order for each operation to accomplish the specific spreading pattern. The controller minimizes distance traveled by the spacecraft and/or spreading time. The spreading spacecraft is autonomous and capable of navigating a predefined spreading pattern based on location feedback from the on-board GPS sensor and computerized control of the spacecraft's throttle and steering mechanisms. Accordingly, the user in the Control Center may provide spacecraft operating parameters (e.g., speed, coordinates, directions, spreading time, amount, etc.) and the controller's processed instructions include when and where to turn home to Earth, etc.). In such an arrangement, the controller's processed new suggested order is presented to the user prior to operation such that the user can accept, reject, or modify the suggested order. For example, the user may wish to avoid spreading in certain areas and modify the suggested Sun barrier accordingly. Alternatively, the user may provide a new specified spreading pattern and coordinates for creating a Sun barrier during step 722 (e.g., by drawing a Sun barrier over the provided map data via a user input and by indicating where substances are to be placed or how controller is to determine where substances are to be placed).

Further referring to FIG. 7C, the controller navigates the spacecraft through the spreading pattern (step 724). The user is presented the processed spreading pattern and already created Sun barrier on a display screen on the Control Center on Earth. The controller operates the spacecraft such that the spacecraft spread the substances after the instructs the spacecraft must follow to begin the spreading process. The spacecraft follows the spreading pattern, the spacecraft is configured to spread substances in the Sun barrier according to the processed spreading pattern. The controller of the spreading system communicates with a spreading mechanism of the spacecraft and instructs the spreading mechanism to place substances when the spacecraft's determined location matches a location of the map data where a specific amount of substances is to be placed. The spacecraft's location is determined based on feedback received from a location sensor (e.g., a GPS receiver). The controller is further configured to adjust parameters of the spreading mechanism (e.g., the flow per unit of time of selected substances, direction etc.) based on the processed spreading pattern. As substances are spread/placed into the Sun barrier, the map data is updated to include the location of the new spread substances (step 725) in the Sun barrier.

After the spreading pattern is completed, the updated map may be saved to memory of the controller of the spacecraft and exported (step 726). The updated map data includes previously detected Sun barrier characteristics and placement of new substances. The map data may be used for future Sun barrier processing (e.g., determine effect of different substances or effect of different amount of substances, determine where and quantity for the next spread, etc.). Accordingly, the updated map data may be exported to an external computing device via a network interface of the controller or can be stored on removable storage media (e.g., SD memory card, MicroSD memory card, USB flash memory, etc.). The user in the Control Center can then access the map on an external computing device, and calculate the obscuring effect of object or area and calculate weather forecasts based on the obscure effect.

Space mapping systems are not limited to spacecraft-based systems (e.g., system 200, 400 and system 600).

Referring to FIG. 8, a stationary radar system 800 is shown in accordance with an exemplary embodiment. The system can include high resolution cameras and for different wavelengths, and for example operate according to the principle used for space telescopes to identify different gases of planets in other solar systems, etc. System 800 includes a camera and radar unit 801 mounted on tower 802. Radar unit 801 is configured to detect intrinsic and extrinsic characteristics of Sun barrier 803 in a similar manner as radar unit 5 of system 200 and as radar unit 403 of system 400 and radar unit 604 of system 600. Accordingly, radar unit 801 utilizes radar to determine characteristics of Sun barrier 803. As transmitted radar waves travel through Sun barrier 803, portions of the wave are reflected back at different strengths depending on the composition of Sun barrier 803 and the presence and depths of substances within Sun barrier 803. System 800 can detect changes in Sun barrier characteristics (e.g., size, composition, density), the presence of specific substances for example, water, the depth of water in the cloud, the amount of water, the presence and type of minerals, and other Sun barrier characteristics. In an alternate configuration, radar unit 801 transmits unmodulated continuous-wave signals that are used to create a plan-view hologram of Sun barrier 803. In another alternate configuration, reflection is used to transmit acoustic waves through Sun barrier 803, and reflected acoustic waves are analyzed to determine the composition of Sun barrier 803 and the location of objects within Sun barrier 803. Feedback signals from radar unit 801 are provided to a controller similar to controller including a processing circuit having a processor and memory (similar to controller 420 and controller 610). And all collected information is sent to Control Center 804 for further analysis and processing. And a location sensor can be coupled to the radar sensor, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine a specific location of the radar sensor and of the extrinsic sun barrier characteristic, based on the specific location scanned by the radar sensor and the distance and angle to the different parts of the Sun barrier;

Radar unit 801 of system 800 is stationary, and therefore has a limited and relatively static area of detection. Referring to FIG. 8, an exemplary layout of Sun barrier 803 is shown. To achieve proper coverage of an area of Sun barrier 803, a user can install multiple systems to cover the area. The areas of detection may be made to overlap to ensure maximum coverage. Each system 800 reports detected Sun barrier characteristic data from the respective area of detection on a regular schedule or on demand. The reported Sun barrier characteristics are sent to a central controller or computing device. Alternatively, each system stores detected data, and a user manually collects the data (e.g., by downloading data through a network interface in communication with the individual controller of each system 800, by downloading data from each system onto a removable storage medium, etc.). The collected information is then used to calculate the effect and whether it needs to be spread more or less, etc., as well as to calculate weather forecasts by calculating the cooling effect the Sun barrier has on Earth and how this will affect the climate and local weather, as well as to what extent it reduces the risk of natural disasters during the project.

The above systems and methods can be operated as part of a business. The business offers may consist of protecting the selected object or area from harmful particles, and may, for example, consist of agreements to disperse a certain amount of certain type of particles at a specified time or time interval at specific coordinates in a specific orbit around the Sun. The business offers may also include an insurance policy to provide a fixed protective effect over specific object or area against payment. And calculated as a percentage reduced risk of damage to what is insured. Here, as a basis for the calculation, the reduction in the number of specific types of particles that have passed through the Sun barrier can be used, by measuring the number both before and after they have passed the Sun barrier, and which travels in the direction of said objects or area that are desired insured. And taking into account the future protective effect decided during the life of the insurance, for example whether the protective effect should be kept constant or increased or reduced.

The business offer may also include protection against specific disasters or the extent of disasters of some severity, such as ice melting, tropical storms and other whirlwinds, forest fires, raising water levels in the oceans, raising temperature in water, air, or soil. The business offers can also cover insurance of substances, supplies and equipment for all stages and include, for example, manufacturing, transport, quality, and delivery reliability. The business offers may also include insurance of the equipment used to fill the spacecraft with supplies, substances, and fuel. The business offers may also include insurance against particles from solar storms causing damage of a specific type or extent to, for example, satellites in an orbit around the Earth or on travel to, for example, the Moon or Mars. The business offers may also include, for payment, scattering the ashes of deceased or deceased pets from said orbit around the sun, where the ashes, or specific substances in the ashes, are ground to the desired grain size and scattered in the same way as other ground materials, such as carbon, or ash from other combustion.

The business offers may also include training, and training to perform the tasks necessary to perform and manage any of the components of the invention. For example, for the manufacture, repair, and maintenance of the rocket as well as personnel at the Control center and the manufacture of substances. The business offers may also include salaries for staff working for the Control Center and for those who manufacture or transport the spacecraft, substances, supplies, software, spare parts, etc. The business offers may include insurance of all personnel and crew working with any of the components of the invention. The business offers can comprise to use a shading effect over specific objects or area for weather forecasts against payment. Where, for example, the shading effect over, for example, specific location or area for a specified period of time is known or calculated, and can be stated, for example, as a percentage reduction in solar radiation. Where it can then be calculated what effect the reduced solar radiation has on the temperature in, for example, air, water, and soil, and how this affects, for example, cloud formation, air currents, precipitation and, with the constitution in this, provide more accurate weather forecasts in all places on, for example, earth. The business offers can also include a Sun barrier mapping services to customers who want to process the cloud's geographical distribution and density in different locations in the cloud as well as its speed and direction of movement in real time. Customers can purchase individual maps of an area of Sun barrier. Alternatively, customers can subscribe to recurring maps (e.g., a new map every day, or a new map every week, etc.). The maps can be used for Sun barrier operations (e.g., spreading operations in the path, harvesting operations depending on predictable weather, etc.). Additionally, the maps can be used to calculate future needs for substances and, for example, that specific substances should be used in specific locations in the cloud and the like. All of the above-mentioned services are provided to customers for a fee.

Although the above systems and methods refer to the spreading of substances, it should be understood that the above systems and methods may be used to spread substances at various form. Accordingly, instead of a substance spreading mechanism (e.g., spreading device 202 or spreading device 502), a substance spreading mechanism can place substances of various size in specified and precise locations. And the spacecrafts can in addition drag a blanket or foil. The construction and arrangement of the systems and methods as shown in the exemplary embodiments are illustrative only. Although only a few embodiments of the present disclosure have been described in detail, those skilled in the art who review this disclosure will readily appreciate that many modifications are possible (e.g., variations in sizes, dimensions, structures, shapes and proportions of the various elements, values of parameters, mounting arrangements, use of materials, colors, orientations, etc.) without materially departing from the novel teachings and advantages of the subject matter recited. For example, elements shown as integrally formed may be constructed of multiple parts or elements.

The elements and/or assemblies of the enclosure may be constructed from any of a wide variety of materials that provide sufficient strength or durability, and in any of a wide variety of colors, textures, and combinations. Additionally, in the subject description, the word “exemplary” is used to mean serving as an example, instance, or illustration. Any embodiment or design described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments or designs. Rather, use of the word “exemplary” is intended to present concepts in a concrete manner. Accordingly, all such modifications are intended to be included within the scope of the present inventions. The order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments. Any means-plus-function clause is intended to cover the structures described herein as performing the recited function and not only structural equivalents but also equivalent structures. Other substitutions, modifications, changes, and omissions may be made in the design, operating conditions, and arrangement of the preferred and other exemplary embodiments without departing from scope of the present disclosure or from the spirit of the appended claims.

The present disclosure contemplates methods, systems, and program products on any machine -readable media for accomplishing various operations. The embodiments of the present disclosure may be implemented using existing computer processors, or by a special purpose computer processor for an appropriate system, incorporated for this or another purpose, or by a hardwired system. Embodiments within the scope of the present disclosure include program products comprising machine -readable media for carrying or having machine-executable instructions or data structures stored thereon. Such machine - readable media can be any available media that can be accessed by a general purpose or special purpose computer or other machine with a processor. By way of example, such machine-readable media can comprise RAM, ROM, EPROM, EEPROM, CD-ROM or other optical disk storage, magnetic disk storage or other magnetic storage devices, or any other medium which can be used to carry or store desired program code in the form of machine-executable instructions or data structures, and which can be accessed by a general purpose or special purpose computer or other machine with a processor. When information is transferred or provided over a network or another communications connection (either hardwired, wireless, or a combination of hardwired or wireless) to a machine, the machine properly views the connection as a machine-readable medium. Thus, any such connection is properly termed a machine -readable medium. Combinations of the above are also included within the scope of machine -readable media. Machineexecutable instructions include, for example, instructions and data which cause a general-purpose computer, special purpose computer, or special purpose processing machines to perform a certain function or group of functions.

Although the figures may show a specific order of method steps, the order of the steps may differ from what is depicted. Also, two or more steps may be performed concurrently or with partial concurrence. Such variation will depend on the software and hardware systems chosen and on designer choice. All such variations are within the scope of the disclosure. Likewise, software implementations could be accomplished with standard programming techniques with rule-based logic and other logic to accomplish the various connection steps, processing steps, comparison steps, and decision steps.

Claims

PATENT CLAIMS

1. An apparatus for creating a sun barrier in an inner orbit around the sun and the sun barrier configured to protect an object or area with determined location traveling in an outer orbital path around the sun, c h a r a c t e r i z e d in that it further comprising: a control center (1) placed on earth, an automatic flying spacecraft, monitored and controlled by the control center (1), and capable of navigating to a designated spreading location in said inner orbit around the sun, a controller coupled to the spacecraft, a time unit coupled to the controller, a location sensor coupled to the spacecraft, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine the direction of travel, speed, and location of the spacecraft, a spreading device coupled to the spacecraft; and, that the controller instructs the spreading device to spread substances or laser beams at the designated spreading location at a specific time or period and create said sun barrier.

2. An apparatus for creating a sun barrier according to claim 1, c h a r a c t e r i z e d in that it further comprises censors (31) that measure the effect of the sun barrier and that the value from censors (31) is used for at least one of the following; to produce weather forecasts for the protected objects or areas, to regulate the amount or type of substance to be spread from one or several spacecrafts.

3. An apparatus for creating a sun barrier according to any one of claims 1 to 2, c h a r a c t e r i z e d in that it further comprises a sun barrier penetrating radar sensor placed on earth or coupled to a spacecraft, the radar sensor configured to scan the sun barrier material to at least a designated depth wherein the radar sensor is further configured to provide a sensor feedback signal to a controller with respect to an intrinsic characteristic of the sun barrier material; and, a location sensor coupled to the radar sensor, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine a specific location of the radar sensor and of the extrinsic sun barrier characteristic, based on the specific location scanned by the radar sensor and the distance and angle to the different parts of the sun barrier; and, that the controller is further configured to create a map of the sun barrier material based on the sensor feedback signal and the location feedback signal; and, that the map provides information that can be used to determine the effect of the sun barrier and to future requirements for the spreading of substances; and, that the sun barriers determined shading effect and determined future spreading of substances that affecting said effect are used to determine the reduction in the radiation of at least one type of particles from the sun for a period of time.

4. An apparatus for creating a sun barrier according to any one of claims 1 to 3, c h a r a c t e r i z e d in that the sensor feedback signals from the radar sensor and the location sensor are further provided to a control center, comprising; a communication unit coupled to a computer unit including a storage unit and a controller; and, that the storage unit configured to include value for limits of the shading effect and value for the preferred shading effect to be achieved, i.e., reduction in temperature on a specific object or area and or reduction in particle current from the sun; and, at least one temperature sensor placed on the protected object or area configured to provide a temperature feedback signal to the controller, wherein the controller analyzes the temperature feedback signal and correlates the temperature value to in the storage unit stored value for preferred value and limit value; and, at least one particle current sensor configured to provide a feedback signal to the controller wherein the controller analyzes the feedback signal to determine a specific value of at least one type of particles in the particle current and correlates the value to in the storage unit stored preferred value and limit value; and, that the controller determines if the present spread of substances needs to be changed, i.e., increased, reduced, or maintained.

5. An apparatus for creating a sun barrier according to any one of claims 1 to 4, c h a r a c t e r i z e d in that the automatic flying spacecraft (3) further comprises at least one of the following: a rocket engine (7); a sensor in the fuel tank for registering the amount of fuel for rocket engines (7); a container (9) for storing and transporting substances (27); a sensor for registering the amount of substances (27) in the container (9); a spreading device (15) for spreading substances (27), for example, a pump, gas, or a rotating knife; a nozzle (17) connected to the container (9); a heating means (11) for heating substances (27) in the container (9) and the nozzle (17); a combustion chamber (21) to create smoke; a laser (19) to create a sun barrier (29); a solar panel (37); a non-reflective black color applicated at least in part on a spacecraft (3); a colorless substance (27) to create a sun barrier (29); a substance (27) that have at least one color, to create a sun barrier (29); an organic substance (27) to create a sun barrier (29); an inorganic substance (27) to create a sun barrier (29); a map of the sun barrier (29).

6. A use of a sun barrier to create a shading effect on an object or area and reduce the risk of damage and natural disasters in accordance with any one of claims 1 to 5, and where the sun barrier reduces the temperature in matter, soil, air, water and organic life on the protected object or area; and, that the reduced temperature reduces the risk of damage caused of at least one of the following disasters: forest fires, rising sea levels, vortex storms, desertification, ice melting, changing ocean currents, oxygen level in water, heatstroke on living organisms, torrential rains, flooding of rivers, damage to electronics; and, wherein a specific reduction in temperature is determined to result in a calculated lover risk of at least one of said damage or disaster and is agreed and insured.

7. A method for creating a sun barrier orbiting the Sun and protecting an object or area from at least one type of particles from the sun, comprising: placing a control center on earth, the control center capable of communication, supervision and controlling at least one automatic flying spacecraft capable of flying to said orbit by a controller coupled to the spacecraft; and, determine the location, direction of travel, speed, and distance from the sun for said object or area; and, decide location and direction of travel for the orbital path for the sun barrier; and, calculate the travel path for said particle from the sun to be stopped; and, analyze and determine a spreading location where and when the particle from the sun to be stopped will pass the decided orbital path for the sun barrier; and, transporting at least one type of substance in a container with an automatic flying spacecraft to the determined spreading location; and, spreading the substance from the container via at least one nozzle and create a sun barrier orbiting the sun at determined location, time, and speed.

8. The method for creating a sun barrier according to claim 7, c h a r a c t e r i z e d in that the method comprising: determine location for an object or area to be protected in a location system, for example a coordinate system including the sun; and, coupling a controller to a spacecraft capable of automatic flying to an orbit around the sun; coupling a spreading device to the spacecraft, the spreading device configured to spread at least one type of substance or laser beams from an orbital path around the sun and create said sun barrier; coupling a location sensor to the spacecraft, the location sensor configured to provide a location feedback signal to the controller, and wherein the controller analyzes the location feedback signal to determine the direction of travel, speed, and location of the spacecraft; and, coupling a time unit to the controller, wherein the controller is configured to: determine a designated spreading location based on the sensor feedback signal and in a storage unit stored information for at least one location from which said substances can be spread at a specific time or period; and, navigating the spacecraft to the determined spreading location in said orbit around the sun; and, instruct spreading of said substances or laser beams and create a sun barrier at the designated spreading location at said specific time or period.

9. The method for creating a sun barrier according to any one of claims 7 to 8, c h a r a c t e r i z e d in that it further comprises a weather modification system supervised and controlled from a control center: the system comprises; evaluation means comprising a computer unit including a communication unit coupled to a storage unit and a controller placed in the control center; communication and data transfer between said control center and at least one automatic flying spacecraft whose controllable means can be monitored, oversteered, and remotely controlled from said control center; and, collecting quantities or a value from a plural of sensors measuring temperature and or particle current from the sun; and, collecting quantities or value from a radar sensor unit for measured size and density on the sun barrier; and, determining the shade effect at any given time by analyzing the collected data from temperature sensors and radar sensor; and, compare the stored desired shade effect with the actual measured shade effect and, in case of deviation, calculate how much substances need to be spread to achieve the said desired values; and, sending control signals to one or more spacecraft to change the amount of spread substances to the new value; and, use of the calculated shade effect and the effect of the planned spread of substances to calculate the total shade effect over a period of time; and, use of the total value from said calculated shade effects to calculate weather forecasts for all or part of an object or area.

10. The method for creating a sun barrier according to any one of claims 7 to 9, c h a r a c t e r i z e d in that at least one of the substances to create the sun barrier comprises at least one of the following: an organic substance; an inorganic substance; a substance that has at least one color; a substance that is colorless.

11. A product in the form of a sun barrier that shades an object or area from particles from the sun and produced according to any one of claims 7 to 10.