FR3088622A1 - Method and device for combating global warming - Google Patents

Abstract

Method for modifying the temperature on the surface of a star known as a shaded star subject to the radiation of at least one second star known as a radiating star characterized in that at least two devices are used situated substantially between the radiating star and the star shaded in order to reduce the intensity of the radiation on the shaded star and in that the number of devices by the surface controlled by each of them makes it possible to make a shade making it possible to control at least one element of the temperature of the star shady

Description

the present invention relates to a method and devices for reducing global warming. In the rest of this text, the term radiant star is used for the star which sends a radiation which heats the atmosphere of a star known as a shaded star, the object of this invention being to bring about a reduction in reception of this radiation. on the shaded star by filtering part of this radiation; in a specific case of implementation of the invention, the radiant star is the sun and the shaded star is the earth;

A solution is known to reduce sunshine on earth from the sun, patent application GB2446250, A dust-or particle-based solar shield to counteract global warming, which is an integral part of the description of our invention. :

However, this solution has the following drawbacks:

- the plume is denser in the center than on the edges,

- enough energy is required to implement the process,

- a large reserve of particles is required to implement the process,

- the emitted particles pushed by the solar wind end up arriving in the Earth's atmosphere at least in part and come in particular to obstruct air traffic, as during volcanic eruptions;

the invention aims to remedy these drawbacks; and it is characterized in particular by the following method, presented in the form of claims for greater clarity:

1) Method for modifying the temperature on the surface of a star known as a shaded star subject to the radiation of at least one second star known as a radiant star characterized in that at least two devices are used situated substantially between the radiant star and the shaded star in order to decrease the intensity of the radiation on the shaded star and in that the number of devices by the surface controlled by each of them makes it possible to make a shade making it possible to control at least one element of the temperature of the shaded star (for example, 128 devices which each control 100 square km of surface make it possible to control the temperature of 1% of the earth, enough to modify the climate of this one, the control being able to be carried out in one direction or in the other for the temperature of the atmosphere of the star to be shaded)

2) Method according to claim 1 characterized in that the at least two devices are coordinated.

3) Method according to any one of the preceding claims, characterized in that the devices are placed substantially on at least one of the Lagrange points located between the so-called shaded star and the said radiating star.

4) Method according to any one of the preceding claims, characterized in that at least one of the devices is shifted towards the radiating star so that the increase in the gravity of the radiating star at least partially compensates the thrust exerted by the solar winds coming from the radiant star on the elements which make it possible to shade the shaded star (particles, solar veil, balloon etc);

5) Method according to any one of the preceding claims, characterized in that the trajectory of at least one device is oscillating around a position (so as to distribute the shade cast more uniformly on the shaded body).

6) Method according to any one of the preceding claims, characterized in that at least one of the devices emits particles to reduce the radiation.

7) Method according to claim 6 characterized in that one uses the instability proper to the Lagrange point where the at least one device is located to make a halo of particles (which distributes the particles around a halo around the equilibrium point emitted by the devices).

8) Method according to any one of claims 6 or 7 characterized in that at least one of the nozzles of one of the devices which emits particles is controlled so that the result of the reaction corrects the position of the device .

9) Method according to any one of claims 6 to 8 characterized in that at least one of the nozzles of one of the devices which emits particles is controlled so that the result of the reaction allows a particular trajectory.

10) Method according to any one of claims 6 to 9 characterized in that it supplies particles at least the device emitting particles from another celestial body than the shaded star.

11) A method according to any one of claims 6 to 10 characterized in that the particles are sent from another celestial body whose gravity is less than that of the shaded star.

12) A method according to any one of claims 6 to 10 characterized in that at least a portion of the nozzles are deactivated during other operations performed substantially from one of the Lagrange points (deactivation of the nozzles to be able to perform measurements for example)

13) Method according to any one of claims 6 to 12, characterized in that the geometry of the nozzles is adapted as a function of the position of the support devices so as to be able to control the fluxes of the particles (for example to make a measurement).

14) A method according to any one of claims 6 to 13 characterized in that the result of the attractive forces pushes the emitted particles towards the radiant star (so as not to disturb the atmosphere of the shaded star).

15) Method according to any one of claims 1 to 5 characterized in that at least one of the devices is a solar sail.

16) A method according to claim 15 characterized in that the orientation of the sail takes into account the radiation and forces exerted on it to be substantially stable with respect to a reference frame of radiating star / shaded star (so as to spend the minimum of energy to maintain a reference position between the radiant and the shaded celestial body).

17) Method according to any one of claims 1 to 5 characterized in that at least one of the devices is a balloon.

) Method according to claim 17 characterized in that the surface of the balloon stops part of the radiation from the radiating star.

19) Method according to claim 17 characterized in that the balloon can be inflated or deflated to modify the surface stopping part of the radiation from the radiating star.

20) Method according to any one of claims 17 to 19 characterized in that the balloon is partly transparent to the radiation of the radiating star and that the reflective power of the balloon is at least partly a function of the gas contained in the balloon.

21) Method according to any one of claims 1 to 5 characterized in that the stopping of the radiation of the radiating star is at least partly obtained by the ejection of elements following an explosion.

22) Method according to any one of claims 1 to 21 characterized in that at least one device is photovoltaic.

23) The method of claim 22 in that waves are returned to the shaded body to recover energy.

24) Method according to claim 22 in that the recovered energy participates in the positioning energy of at least one device.

25) Method according to any one of claims 1 to 24 characterized in that at least one device releases elements which are solidified by means of a particular process (for example plastic which is hardened with a laser).

The invention relates to the method as described above, the device (s) for implementing it, the system for implementing this invention, the program instruction (s) operable by one or more computers or data processors for implementing implement the method as described above as well as the data carrier (s) readable by a computer or data processor, and comprising instructions of a program as mentioned above.

More specifically,

A) it suffices to decrease by 1% the radiation arriving on the shaded star to modify its atmosphere:

extract science et vie of October 2018, page 68: “some scientists are considering a shock treatment: each year inject millions of tonnes of sulfur particles into the stratosphere, about 20 km above sea level, to block part of the solar radiation - of the order of 1%. A treatment directly inspired by major volcanic eruptions, such as that of Pinatubo which, in 1991, had cooled the world atmosphere by about 0.4 degrees by simple parasol effect "end of the extract.

calculation of 1% of the shaded surface of the shaded star if the latter is the earth and we consider that the radiant star is the sun:

000,000 meters in diameter for the earth / 3.14 = 12,738,853 / 2 = 6,369,426 which is rounded down to 6,400,000 m

Pi R2 to have the maximum area to be shaded: 1,286,144,000,000,000 square meters.

It is necessary to shade that 1/100 of this surface is:

= 1286144000000 m square

B) First solution for shading the shaded body: projection of particles:

If each nozzle can send particles to cover an area of 100 km squared equivalent to

100,000 * 100,000 = 10 power 10

It takes 128 devices distributed in the space to shade the shaded star. FIG. 1 represents an example of devices comprising nozzles for ejecting particles, with sends in several directions of particles, placed between the radiating star and the star to be shaded and constitutes a particular embodiment of the invention (on this figure we have only represented a part of the nozzles but the skilled person understands very well how to distribute 128 devices between the two stars to ensure shading of the shaded star).

C) second solution for shading the shaded body: use of balloon (s);

If for example we take a balloon of 350,000 m ² of equivalent surface (shadow cast on the shaded star) the number of approximate necessary balloons (they are not square) is 3,674,697, or approximately 3 million balloons. If we only take into account the two sunniest hours of noon in Figure 2, for the legend, refer to document GB2446250, we divide by 2 the area required, which equals 1.5 million balloons;

To reduce the number of devices to be positioned in space, the skilled person understands that the assembly of these devices from a star of lesser gravity than that of the shaded star, makes it possible to send into space larger devices, therefore fewer in number to cover the same surface.

D) third solution for shading the shaded body: solar sail (s)

The technical sheet [online] .wikipedia, 2018 [extracted on 1998-11-13]. Extract from <https://fr.wikipedia.Org/wiki/Sunscreen> is an integral part of the description; it can be noted in particular in this document, that:

“To accelerate 1 kg of I m / s ² , we therefore need at least a surface area of 106,383 m ² , ie a square of 326 mx 326 m, the mass of this sail being to be deducted to obtain the payload. A sail of this size using less than 1 kg of material would immediately rupture on Earth under any draft of air, but this problem obviously does not exist to this extent in space. "

This document also describes the forces that the solar winds can exert:

"

Importance of solar wind

We can also think of the solar wind (flow of electrically charged particles, sent out of the Sun) as a contribution to the phenomenon. Here is a little calculation to fix the ideas.

The characteristics of the solar wind at Earth level are:

Particle speed around 500 km / s = 5 x 10 ⁵ m / s.

Density about 10 particles per cubic centimeter, or 10 ⁷ particles per cubic meter.

In a second and over 1 m ² , it therefore arrives N = 5xl0 ⁵ x 10 ⁷ = 5xl0 ¹² particles.

The composition is variable, but essentially contains electrons and atoms of ionized hydrogen (i.e. protons). The mass of each particle can be estimated at: m = 2 x 10 " ²⁷ kg.

If they bounce completely on the sail, each will transmit to the sail an impulse equal to twice its own, i.e. p = 2 mv = 2 x 10 ²¹ kg ms ^-1 .

The acceleration undergone by 1 m ² is therefore: a = N xp / 1 s = 10 ' ⁸ m / s ² .

All of this is a high estimate. If we compare to the radiative pressure found previously (5x10 ⁶ ), the solar wind contributes at best only 0.2% of the total. And, in fact, if we take into account the proportion of electrons (half the flux), the more the rounding, the lower the reflection of the ions, which will rather become embedded in the sail, we could at least divide by 4 this order of magnitude, that is to say ultimately a contribution of the order of 0.05%, which is to say negligible.

Design

NASA study of a solar sail. The sail would be 500 meters wide.

It is therefore understandable that the surface offered by the sail is a primordial characteristic in the performance of this propulsion means (a 110,000 m sail is necessary to obtain a thrust of I kg m / s). The difficulty will then be to transport this sail during the putting into orbit of these machines, to deploy it and to steer it in space vacuum. "

The following extract from this wikipedia file allows us to extrapolate the surface of a 10-ton solar sail:

"

Achievements

Several solar sails have been launched into space or are under study or under development. These are prototypes intended to develop the various systems specific to this type of propulsion, in particular the deployment of the sail and the orientation of the thrust. IKAROS is a solar sail developed by the Japanese space agency, the J AXA, launched in 2010 and still operational in 2014. Its surface area of 173 m ² allows it to change speed up to 12 m / s after one month . With a total mass of 315 kg, including 2 kg for the solar sail, it circulates in a heliocentric orbit of 10 months. NanoSail-D2 is a small 10 m ² solar sail made for NASA and which was launched in 2011. The continuation of this project is Sunjammer, a 1200 m ² solar sail, which was to be launched in 2015 but whose development was arrested in 2014. Finally LightSail-1 is a 32 m ² solar sail developed by the Planetary Society and whose launch is planned for 2016. "

So if a 2KG solar sail is 173 m square, if you use a 10 ton satellite you get a solar sail area of 850,000 M square, that makes about 1 million devices to put into orbit;

To reduce the number of devices to be positioned in space, the skilled person understands that the assembly of these devices from a star of lesser gravity than that of the shaded star, makes it possible to send into space larger devices, therefore fewer in number to cover the same surface.

An alternative to sending in space blackout solid devices to shade the shaded body is to manufacture on the spot these blackout solid devices, for example by solidifying by means of a laser plastic particles emitted in space.

E) ° positions of the devices for shading the shaded star the Lagrangian points are the points where, concerning the earth and the sun, the gravity of the sun and the earth cancel each other;

The technical sheet [online] .wikipedia, 2018 [extracted on 1998-11-13]. Extract from <https://fr.wikipedia.org/wiki/Point_de_Lagrange> is an integral part of the description; it can be noted in particular in this document that:

A Lagrange point (noted Li to L ₅ ), or, more rarely, libration point, is a position in space where the gravity fields of two bodies in orbital motion around one another, and of substantial masses, provide exactly the centripetal force required for this point of space to simultaneously accompany the orbital movement of the two bodies. In the case where the two bodies are in circular orbit, these points represent the places where a third body, of negligible mass, would remain motionless compared to the other two, in the sense that it would accompany at the same angular speed their rotation around their center of common gravity without its position in relation to them changing. Five in number, these points split into two stable points called L4 and L5, and three unstable points denoted Li to L3. They are named in honor of the French mathematician Joseph-Louis Lagrange ¹ . They are involved in the study of certain configurations of objects in the Solar System (mainly for stable points) and in the placement of various artificial satellites (mainly for unstable points). These are the remarkable points of the “Roche ² geometry” (col-points and extrema), which notably makes it possible to classify the different types of binary stars.

The three points L _b L ₂ and L ₃ are sometimes called the Euler points, in honor of Leonhard Euler, the name of Lagrange points then being reserved for the two points L ₄ and L ₅ ³ . Figures 3 and 4 represent these 5 Lagrange points.

The mathematical study of Lagrange points, as well as their mathematical properties, such as the associated invariant varieties, could be used for the design of missions for satellites in the solar system. For missions like Rosetta, Voyager or Galileo, the relative speed of the satellite with respect to the bodies considered is sufficiently high that the approximation considering that the Keplerian orbits are only slightly disturbed by the other bodies within the sphere of influence . However, as soon as low speeds and low thrusts are considered, a finer approximation is necessary. Lyapunov-Poincaré's theorem assures us of the existence of a family of periodic orbits around these equilibrium points. The planar periodic orbits are then called Lyapunov orbits, while in the 3D case, they are called according to their topological properties, either Halo orbits or Lissajous orbits. It can be noted that this type of periodic orbit around the Lagrange points has already been used in the construction of real missions such as the SoHO mission.

From these periodic orbits around the Lagrange points, come invariant varieties (Conley-McGee tubes) which are separators of the dynamics, and which in this sense can be considered as gravitational currents. Increasingly, these currents are used for mission design, notably with the Interplanetary Transport Network (ITN).

Lagrange Points are used to meet the specific needs of certain space missions:

• The Lagrange point L ₂ of the Earth-Sun system, distant from the Earth, allows to benefit from a great thermal stability while being located sufficiently close to the Earth (1.5 million km) so that the collected data can be transferred with a high flow to Earth. It is used in particular by the large space astronomical observatories launched during the last two decades: Planck, James-Webb, Gaia • The Lagrange point Lj of the Earth-Sun system, located closer to the Sun than the Earth and the Moon, makes it possible to observe the Sun without interference from these celestial bodies and to detect solar disturbances before they reach the level of Earth's orbit. It is the ideal position for space weather missions like the one fulfilled by SoHQ.

• The Lagrange point L2 of the Earth-Moon system was used for the first time by the Chinese satellite Queqiao because this telecommunications satellite from this orbit can retransmit towards Earth the data collected by a machine placed on the far side of the Moon .

The points L ₄ and L ₅ are generally stable, so there are many natural bodies, known as Trojans:

Figure 5 illustrates the stability of the Lagrange points.

In the Sun-Earth system, known since ¹ October 2010 a Trojan developed L4,1 asteroid 2010 TK7, which measures 300 meters in diameter ^5,6,7. Some astronomers point out that this object could represent a risk comparable to NEOs. These authors also propose that the impactor supposedly at the origin of the Moon (Théia) would have stationed a time on the point L4 or L ₅ and accumulated mass before being ejected from it under the action of the other planets.

Applications

The points L] and L ₂ are unstable equilibria, which makes them usable in the context of space missions: there are no natural bodies there, and a dynamic balance can be maintained there for reasonable fuel consumption (the gravitational field being weak in their vicinity).

The main advantages of these positions, compared to Earth's orbits, are their distance from the Earth and their exposure to the Sun constant over time. The Li point is particularly suitable for observing the Sun and the solar wind. This point was occupied for the first time in 1978 by the ISEE3 satellite, and is currently occupied by the SoHO, DSCOVR, Advanced Composition Explorer and Lisa Pathfinder ⁹ satellites. Conversely, the point L ₂ is particularly interesting for observation missions of the cosmos, which embark on highly sensitive instruments to be diverted from the Earth and the Moon, and operating at very low temperature. It is currently occupied by the Herschel, Planck, WMAP, Gaia satellites and will be occupied by JWST in 2Ο2Ο ¹⁰ .

A person skilled in the art can understand that the solution can also protect from radiation from the star radiating an celestial body without atmosphere, for example to reduce the radiation on its surface, prevent the solar winds from tearing off its atmosphere, or reduce its temperature to ground or at a certain altitude.

The following documents are also an integral part of this description:

- patent application W02009104496 Apparatus for expelling energy away from the earth in order to suppress global warming,

- US patent 6,723,912 B2: space photovoltaic power generation system;

Claims (10)

1) Method for modifying the temperature on the surface of a star known as a shaded star subject to the radiation of at least one second star known as a radiating star characterized in that at least two devices are used located substantially between 1 radiating star and the shaded celestial body in order to reduce the intensity of the radiation on the shaded celestial body and in that the number of devices by the surface controlled by each of them allows to make a shade allowing to control at least one element of the temperature of the shaded star. 2) Method according to claim 1 characterized in that the at least two devices are coordinated. 3) Method according to any one of the preceding claims, characterized in that the devices are placed substantially on at least one of the Lagrange points located between the so-called shaded star and the said radiating star. 4) Method according to any one of the preceding claims, characterized in that at least one of the devices is shifted towards the radiating star so that this 1 increase in the gravity of the radiant star at least partially compensates for the thrust exerted by the solar winds coming from the radiant star on the elements which make it possible to shade the shaded star. 5) Method according to any one of the preceding claims, characterized in that the trajectory of at least one device is oscillating around a position. 6) Process according to any one of the preceding claims, characterized in that at least one of the devices emits particles to reduce the radiation. 7) Method according to claim 6 characterized in that one uses the instability proper to the Lagrange point where the at least one device is located to make a halo of particles. 8) Method according to any one of claims 6 or 7 characterized in that at least one of the nozzles of one of the devices which emits particles is controlled so that the result of the reaction corrects the position of the device . 9) Method according to any one of claims 6 to 8 characterized in that at least one of the nozzles of one of the devices which emits particles is controlled so that the result of the reaction allows a particular trajectory. 10) Method according to any one of claims 6 to 9 characterized in that it supplies particles at least the device emitting particles from another celestial body than the shaded star.