DE102004004543A1 - Loading and docking station for spaceships with solar sails has inner ring with clips on large ship or station engaging outer ring on docking probe of tug assembling space debris - Google Patents

Abstract

The large ship or space station may have living quarters made of concrete made from collected asteroid rock. The space tugs may have nets or other suitable gear for collecting small asteroids. A tug docking point on the space station has an inner ring (5) with clamps (5.1) and wire winding spools (5.2). The clamps may engage an outer ring (6) on the space tug and have holding forks (5.1.1) with hooked ends and connector portions (5.1.1.1). There are lower (5.1.2) and upper (5.1.3) fastening shells with fastening bolts (5.1.4) and nuts (5.1.6). There is a holder plate (5.1.5) and a stop (5.1.1.2).

Description

With This application will cover the functionality of patent applications filed by 24.07.2002 spacecraft and space structures.

The subsequent application also refers to reference numerals and drawings (in particular 1 ) of the petition.

Docking or charging station

The most important innovation is the in 8th illustrated docking or charging station in the form of an inner ring 5 with attached docking and charging devices, and the associated docking technique described below.

The resulting main application is the transportation of a small, self-powered spacecraft / lander by a larger (solar sailing) mothership to the site and subsequent Re-docking with forward / return transport.

The station is basically nothing but the inner ring 5 comprising a recess in the center of the structure and provided with holding devices for docking, as well as electric winch lifting and clamping devices for loading. Another prerequisite for the docking process is the presence of brackets on the docking unit, this holding function preferably by an outer ring 6 is perceived.

The docking and charging station allows using the inner ring following operations:
Docking and dropping smaller spacecraft,
Recording and decoupling of functional units,
Picking up and dropping cargo,
Recording of charging equipment or equipment for handling objects.

The inner ring is thanks to the tension of the outer ring 1 the spacecraft outgoing tethers 2.1 held in the center of the structure (see 1 of the petition and 8th ). In conjunction with attached winches, it allows safe handling of cargo and other objects that can be safely accelerated and maneuvered by the possibility of clamping in the ring without knocking around.

A another important innovation is the introduction of functional units, they themselves have an outer ring or other mounting options own, which are coupled into the inner ring of a larger carrier unit can.

In order to It is meant to be a functional unit that has a specific purpose Fulfills, such as B. a regolith collecting container or a drill bit to Setting of drilling anchors by equipping with an airworthy drive ring itself transformed into a spacecraft, which is self-sufficient at the place of use (eg an asteroid) and independently on the Mothership on and off.

This allows it, an equipped with an inner ring spacecraft in no time Time by replacing the functional unit or a corresponding equipped Daughter ship for to convert another purpose.

The possibility of docking leaves even a robotic conversion by exchanging different functional units without participation from people too.

So can smaller and lighter for the actual mission purpose optimized units by for the purpose the cost-effective Transport optimized, reusable large solar gliders (the bigger, the bigger faster the transport takes place) are transported to their place of work, to z. B. to gain raw materials of asteroids.

A relatively large solar sail mothership, for example, 100 m in diameter could in the Do ckingstation a sailless subsidiary vehicle with a diameter of z. B. 10 m close to an asteroid approach. The thruster and fuel quantity of this daughter ship would be optimized for the short-term purpose of landing and extraction of raw materials on asteroids.

to execution a novel mission would have only the daughter unit planned, manufactured, launched and may be mounted in outer space while the mothership is out earlier Return missions and can accommodate the daughter unit.

The through the docking station enabled Modularization leaves it to create appropriate standards (size classes) and thereby different organizations, companies, research institutions, etc. Opportunity to give space projects that not only to perform satellite launches, which they lack because of Otherwise means would be closed.

So could such smaller operators quite space projects completely independently design and build, focusing on the specific core projects, so on production and equipment of the daughter ship / daughter unit and its use in space focus.

Responsible for the actual Launching and the provision of a mothership, the transport back and forth to the place of use would be but then specialized in large companies, but better this authorized organizations / agencies.

By once introduced Standards would be Planning security for all parties involved and it would not have to be for each new project always new constructions are developed.

The ESA could z. B. by the provision (also by renting for the respective Mission duration) of infrastructure and transport services in the form of carrier ships, Space stations, material depots and other space structures, which could not be financed by smaller institutions, one Contribution to the start of the European Space technology.

hereby could the diversity and innovative strength smaller companies / institutions through this advance for the development of space.

But also the international exchange as well as the cooperation would go through the introduction corresponding coupling classes and mutual provision compatible infrastructure.

The introduction and separation of airworthy, but not or only limited long-range aircrafts spacecraft as a subsidiary ship and long-range capable mothership would also have another advantage;
The near-earth movement of space projects could be under the control of less, the security of the Earth to a special extent committed organizations, without obstructing access to space to smaller units.

It It is obvious that the threat to the earth is increasing frequency the movements of the air and the increasing number of those over the have appropriate technology, overall enlarged. Therefore would be a certain control or a long-distance transport monopoly through this specially authorized Make quite desirable.

In addition to spacecraft and solar gliders are also completely different types of functional units that can be coupled into inner rings, conceivable, such. B.
satellite,
Drive units,
Mirrors, lenses and parabolic mirrors for transmitting light, heat, energy,
Antennas, satellite dishes, transmission equipment,
Laser systems,
Nets and sacks for collecting space junk and space debris
airworthy material containers,
airworthy material collector for regolith and rock,
flyable payload units,
airworthy repair robots,
Screwdriving and drilling inserts,
Rotary separating or separating and grinding devices,
Concreting and other forms / moldings.

The mothership / ring structure can provide the coupled functional units not only transport services, but also the possibility of connection to the solar cell arrays 2.6 (S. 1 ) of the carrier. The power supply to the daughter ship could via the electrically conductive support forks 5.1.1 in 8th respectively.

hereby would be at least while the transport or use in the mothership the power supply secured to an extent by the daughter unit because of smaller size over one longer period possibly could not be provided.

With the inner ring coupling technique, it is also possible in principle, several Nesting spacecraft or functional units into each other. So could For example, a functional unit with a diameter of 10 m in a Mothership with 100 m diameter can be used that in turn in an even bigger mothership transported with 1000 m diameter.

If still wishes in terms of carrying capacity and speed, which depend on the surface of the sail, should be open also the extension by an additional one Unit possible, the z. B, could have a diameter of 10,000 m.

electromagnetic Coupling and decoupling by means of an annular disc made of ferromagnetic Material as docking inner ring

In the 8th illustrated mechanical docking option could be replaced by a completely magnetic docking device. Here is located at the location of the inner ring of tube material a disc of ferromagnetic material (iron or ferrous material).

Of the outer ring the docking vehicle would be in this case as big as the inner ring of the wearer, both rings would thus lie on each other in the coupling.

The Liability of the docking spacecraft would be controlled by electromagnets, the at the docking side of the outer ring of the daughter unit would be attached generated.

Around not on a permanent basis Turning on the electromagnets to be instructed could be this Coupling device with weaker Permanent magnets combined that are weak enough that overcome the activated thruster of a starting subsidiary unit can.

A another variant would be the combination of the use of permanent magnets and electromagnets, whose poles are aligned so that these when removing from the Repel annular disc.

Mechanical dock mount ( 8th )

in the Basically, the inventor draws a simple electromagnetic Coupling to an inner ring in the form of a magnetic (iron-containing) Ring disc on the mother structure and of electromagnets at the Daughter unit, because this is an easy to control process - the electromagnets The daughter units are switched on when coupling and at Uncoupling switched off again.

These Ankopplungsart should be in the conditions prevailing in space conditions because of the hardly existing gravity in most cases completely be enough.

However, since it is idle to describe the trivial attachment of the existing magnetic material ring disc at this point, is here as a variant of in 8th shown mechanical coupling can be explained by means of inner ring.

This would have advantages as additional protection of the coupled objects, such as in the event of failure Power supply to the solenoids or simply as a power conservation measure, or to enhance the coupling of spacecraft intended to reenter planetary atmospheres.

Also in structures where a particularly light, yet stable execution it is asked for, that would be Use of an inner ring in tube form of z. B. CNT material because of the high load capacity, the relatively low weight of this Materials and the high stability effectiveness of the tube shape preferable with minimum material consumption.

Mounting a mechanical dock mount ( 8th )

In 8th is a mechanical docking solution on an inner ring shown by means of several (in Example 4) docking brackets 5.1 , in which the outer ring of a daughter unit is docked, was realized.

The mounting of these brackets takes place starting from the inside of the ring by passing the free ends of the support fork 5.1.1 both through the tubular body and through one of the mounting clamps 5.1.2 or 5.1.3 who have already prepared wells at the designated locations.

The plug-in process is by a stop 5.1.1.2 limited, the z. B. can be realized in the form of a thickening of the rod or attached to the appropriate location limiting ring disk.

The fixing clamp comprises a part of the tube after insertion of the fork completely (eg the lower half) and forms a reinforcement of the attachment with the second clamp, if both clamps by means of a top-down or from bottom to top screw 5.1.4 and the mother 5.1.6 be pressed around the tubular body of the inner ring.

The externally threaded ends of the retaining fork 5.1.1 be by means of two fork-end screw sleeves 5.1.8 , which have an internal thread and at the head end a stop in the form of a stop edge and through the fork plate 5.1.5 be put on, put on. As a result, the attachment of the holding fork is completed.

The holding device is completed by each attached to the support forks on straps of the daughter unit electric locks 5.1.7 , The attachment of a lock may preferably by screwing an electric lock retaining plate 5.1.9 take place at the bottom of the lock, wherein the belt is clamped between the lock bottom and retaining plate.

Mother-daughter-grandson units as transporter, power supply and landing units (lander / prospector)

One Another application example of the nesting technique would be a transport mothership as a solar glider with z. B. 100 m diameter and a flyable power supply unit of about 10 m in diameter in turn the actual landing craft from Z. B. 5 m diameter is coupled into the inner ring.

So could the lander together with the power supply unit from the mothership at the place of use in the vicinity of the Asteroids are exposed where they then separate as well.

The Landing vehicle would be with batteries that allow it energy by coupling into the power supply unit recharge and / or energy reception facilities (Rectenna or solar cells) with which the transmitted energy of a microwave or laser transmitter unit of the small power station.

A another possibility that would be direct connection of over the asteroid floating power unit with the lander through a power cable of several hundred meters, so that the power supply is always in sunlight.

When Material for the power cable is particularly suitable CNT material (carbon nano-tubes) because of its high tear strength with simultaneous conductivity and insensitivity to Space influences.

Advantage of this solution is that batteries are saved and on the Energieempfangs- and Sendeeinein can be completely dispensed with, in addition, no conversion losses.

The Idea, a power generating unit in space through a cable or by sending the power to a power consumer is certainly not new, z. For example, it has been used in US Patent 6,194,790 B1, in this Case on a satellite.

New however, is the connection of a self-powered lander with the power supply unit and a carrier ship and the possibility each independently to be able to connect and disconnect.

This allows it z. B. the lander over longer To use time on the shadow side of an asteroid while the Power generation unit constantly Power to the lander forward.

Coupling sense rings in big Space structures

One Such inner ring is not only for spacecraft, but especially also for all rotating big ones Space structures to dock on, such as B. space stations, Habitats, power plants (for the production of energy and its transmission to the earth) an important addition.

The Docking device allows it the here described disc-shaped spacecraft with its outer drive ring despite the rotation, even if they are at the same angular velocity how to rotate the main structure.

These Structures ideally have a constant orientation through Rotation can be stabilized. In addition, z / should z. B. habitats and space stations also rotate to generate artificial gravity.

On the other hand stands at another large structure, a space power plant, on the one hand, its solar collectors to the sun and on the other hand the energy to the earth or other objectives by microwave or laser with great accuracy to a limited destination size Must send distances, securing the alignment in the foreground.

One sudden Deviation from the target area, z. B. triggered by the impact with space junk or other objects especially with laser transmission of energy have devastating effects and should therefore be avoided Rotation stabilization can be prevented.

rotating Spinners or gyroscopes, for example, are very heavy in their orientation to dissuade, all the more, if a large part of the mass at the outer edge located (as with outer ring structures) and this outside one Mass center is far away from the center of the disc.

conveniently, The ring-shaped space structures developed by the inventor are currently suitable their characteristics, which correspond in their basic form to a particularly stable gyroscope, excellent for this kind of stabilization.

you Imagine a ring structure with a diameter of several a hundred meters ahead. A gyro of such size at the also a big one or maybe even the largest part the mass in or on the outer ring (eg, the outer thruster units) has never existed before. These extremely enlarged dimensions are responsible for the stability of the alignment A rotating structure's crucial features leave one as well assume extremely stable positional behavior. On top of that, this one Structure in space is not disturbing friction forces is exposed.

Docking process (here on rotating space structures)

One Object that rotates can best be docked in the center, because the probability that the docking vehicle through the Centrifugal force is thrown away, with the distance from the center increasing more and more.

The "shutdown" (stopping) of the rotation particularly massive large objects and subsequent Startup is extremely energy intensive.

However, the need to shut down the rotating object can be reduced by using the In nenringes be avoided as a docking station when the docking spacecraft itself rotates. This not only saves energy, but also z. B. manned space stations normal operation is not disturbed.

This Docking between two rotating objects should in the following be described in more detail.

The docking vehicle, which is preferably a disk-shaped drive ring spacecraft after 1 could position itself over the docking ring at a fixed distance (home position) and even rotate at the same angular velocity as the station.

With the help of the upward-emitting (ion) -thruster 1.6 in 1 , which allow due to their very low thrust rather deliberate maneuvers, the ship approaches gently rotating the station and sets shortly before reaching the docking mounts with the counter-thrust of the downwardly expelling and thus accelerating up thruster 1.6 to minimize docking speed.

One Gentle placement of the spaceship outer ring should be the result to be the previous approach.

Even though the thought of docking a spacecraft that is here in rotation, unusual may appear, the inventor assumes that this is for a rotating Vehicle of the type described here because of the position stabilizing gyro-shaped form is easier than for non-rotating vehicles.

8th shows a spacecraft that is docked with its outer ring in the inner ring of a larger unit. For the larger unit it could be z. For example, a giant solar glider or an annular space station or a material depot or a space solar power plant act.

If both coupling objects are rotationally stabilized when approaching are, probably when they are at a fixed distance (the starting position) parallel with the same angular velocity, continue to have the same orientation at the meeting.

So also in the actual coupling, the final insertion of the outer ring 6 of the docking spacecraft in the on the inner ring 5 the space station attached docking mounts 5.1 ,

The fine alignment of the coupling vehicle could, for. B. by 4 in each 90 degrees away from each other on the outer ring 6 position space transmitters attached to the spacecraft, each at 4 also at 90 degrees on the inner ring 5 of the object to be approached mounted opposite points almost perpendicularly opposite and to a set distance - the basic position - are adjusted.

Has Now each of these four calibrated beacons are exactly the same Distance to the counterpart (eg in the form of a recipient or in the form of a reflector) on the object to be approached and is the reached fixed distance and rotate both objects with the same angular velocity, the spacecraft is in the home position and the approach can kick off.

• a) Das Andockobjekt platziert sich in einer festgesetzten Entfernung genau parallel zum Mutterschiff bzw. der Station oder des Objektes oder des Raumschiffes über dessen Zentrum.
• b) Die Rotationsgeschwindigkeit wird angeglichen.
• c) Die Annäherung wird durch gleichzeitiges Zünden der nach unten schiebenden Thruster eingeleitet.
• d) Vor dem Auftreffen werden die nach unten ausstoßenden Thruster solange gezündet, bis die Annäherungsgeschwindigkeit fast auf Null gesunken ist. Das Auftreffen erfolgt dann sanft mit der noch verbliebenen Restgeschwindigkeit.
• f) Die Bolzenriegel der Magnetschlösser 5.1.7 schieben sich unter der Halterungsgabel 5.1.1 hindurch über das Rohr des Außenringes 6 und befestigen somit das ankoppelnde Objekt.

For this purpose, the individual phases of the docking process are described below:

• a) The docking object is placed at a fixed distance exactly parallel to the mothership or the station or the object or the spacecraft over its center.
• b) The rotation speed is adjusted.
• c) Approaching is initiated by simultaneous firing of the thrusters pushing down.
• d) Prior to impact, the thrusters that fire downwards are ignited until the approach speed has dropped to almost zero. The impact then gently with the remaining residual speed.
• f) The bolts of the magnetic locks 5.1.7 slide under the support fork 5.1.1 through the tube of the outer ring 6 and thus secure the coupling object.

at a later one The locks of the magnetic locks are retracted again and put down The daughter object can start its thruster and initially straight accelerate upwards before turning it in the desired direction.

"Flying Space Cooper" as a space junk and rubble collector, to increase satellite orbits with trawl or bag as well as a catch unit for mass-driver transport - s. 9 and 9.a -

Because of Impact hazard should be the environment of space facilities, such as z. B. solar power space power plants or space stations, as well as often used trajectories especially in front of flying debris, space junk and the like protected become.

The best possibility, is certainly such debris not to arise. However, this is not always possible. One good compromise would certainly be to oblige the polluters to at least their scrap or their debris to dispose of in the vicinity of the earth itself, or disposal to pay by appointed institutions.

A easy way performing such tasks would be a flying ring spacecraft, that consists of little more than a drive ring and an in this hung up Net or a bag-shaped or collector bag, with which the spacecraft collects the space junk.

Control, Receiving and transmitting units and cameras of this spacecraft would be with similar brackets similar as the Thrust units attached to the outer ring.

So long the flying butcher forward accelerated, the trapped objects are accelerated by the pressure kept in the network.

faster the butcher suddenly in the opposite direction, which easily gives him the opposite direction the double tube units possible is, the captured objects move at the previous speed continue in the direction previously followed and leave the network / the Käscher again.

Consequently could the space junk elegant z. B. by collision course in the direction Moon be encountered and thus disposed of on this, while the Käscher finished his collision course and further scrap for disposal collects.

For such a Vehicle would be it with appropriate size also no problem catching satellites and then on to transport another orbit, ie mostly around the orbit track to increase again.

Compared to the hereinafter described by Orbital Recovery Docking process where the docking recovery spacecraft itself on a satellite without this provided docking device must attach, this would be not the risk of drifting or becoming unmanageable Rotation of the satellite.

A another option is the insertion a net / sack / cashier as a functional unit in the inner ring of a solar glider or spacecraft. By using a solar glider, the duration of use is considerable elevated, before the replacement of the spent Thrustereinheiten (with the so related Fuel tank) is required.

When Material for the trawl or tow bag is proposed as a fabric of carbon nanotube fibers (CNT), but at least carbon fiber reinforced composite fabric.

Of the Advantage of this crusher / and sack spacecraft is the easy way by collecting material or objects and, if necessary, disposing of them, without that special collection equipment such as B. robot arms would have to be used.

A further use such a flying laundry bag / sack that would be Recording and transport of z. B. on asteroids or moons recovered raw materials.

So could the SSI mass driver concept, in which ferromagnetic objects or Raw materials hurled into space using magnetic rails be, in such a chipper, who retrieves the hurled objects at his destination, his ideal supplement Find.

So promoted ores, or metal-bearing rocks from the place of origin to the destination or be transported to a distribution node, without the need for spacecraft.

A another possibility would be that Mass-Driver Slings of magnetic material containers around z. B. dusty and sandy To transport raw materials. An essential additional The advantage is that these containers also non-magnetic materials can transport and that with a transmitter and possibly a rudimentary thruster drive could be equipped which simplifies both position determination and trapping.

9.a shows a flying butcher (mainly intended for collecting space debris and increasing satellite orbit) 9.b shows a flying sack, which is rather intended for use as an airworthy raw material collection container.

Carrier ship with inner ring as Repair and maintenance unit and towing equipment

One equipped with an inner ring spacecraft or solar glider could with a flyable Repair unit equipped to serve as a workshop unit. These would out a flyable Thruster ring with fitted in it Tool / spare parts and waste containers exist on which the upper body a repair robot is attached.

This Repair robot would have preferably 4 arms, as he has outdoor repairs or maintenance (eg, replacement of the thruster units) in which he is holds on the repair object with two arms and with the two other arms and hands repaired.

The second pair of arms is so important because in the weightless room every little thing contact a push off can cause the object to be serviced or repaired and also the possibility must be given to exercise back pressure.

Definitely would be too an attachment by lines, anchors, magnetic lines u. Ä. conceivable. The solution with the second arm pair and flyable But subset seems to be the most practical.

One further requirement for a human-controlled robotic repair unit would be two Cameras attached to a head-like structure. hereby could a human visual impression for the Remote control by means of virtual reality control by human Astronauts arise.

In First and foremost, this maintenance unit is meant to be one of a kind Space fleet of solar gliders and spacecraft with thruster ring to wait for this patent application, in particular so the pluggable thruster units according to claim 8) of the petition to exchange and since these simultaneously are provided with a tank, thereby simultaneously "refuel".

Also refueling with an outboard Tank connection provided larger thruster units could be made by such maintenance robot with Thrusterring.

in the Ideally would So the individual units of a fleet no longer for maintenance or return to a space station to pick up fuel, but they would from the maintenance ship, which also represents a spare parts warehouse, visited on site. By waiting for several ships that become in spatial Close to each other could be therefore return times be saved.

On the carrier ship entrained Spare parts, such. As solar cells, thruster units, solar sail and Ring segments allow for a further extension of the service life.

Should the need to tow objects could also be the use of 3 staggered units take place, for. B. two solar gliders and the repair function unit, the repair unit the coupling of the largest unit with the towing property and then again with the second smaller one Thruster sailor coupled and can take the way back separately.

Use of the inner ring for space tractors (space tug) and charge transport

Due to the inner ring, which can take on very large dimensions quite considerable dimensions, (such as a 1000 m spaceship with 100 m or 200 m inner ring), it is possible objects such. B. satellites or small asteroids in the center of the spaceship and in a different direction to be to accelerate without the objects held in the ring suddenly developing their own life.

Of the Inner ring offers thus by the secure attachment of the cargo the possibility, the spacecraft also with recorded load without complications to steer.

at the steering is just the big one Lever the thruster on the outer ring of the spacecraft when the cargo is in the center, help. supports Such a clamping action by the use of the inner ring mounted winches with appropriate holding tool, such. As ropes, straps, magnets, retaining rings, snap hook, u. Ä., where the winches provide a tight tension by appropriate tightening can.

Inner ring winches with different functions ( 8th )

In 8th are 4 electric winches 5.2 presented with 4 different functionalities. The inclusion of four differently equipped winches was only to illustrate the different uses.

Of course it makes more sense, at least two, ideally 4 to have similar winches for secure attachment inside the structure. By appropriate tightening of the winches so that a uniform tension is created for each individual, the loads to be transported can be safely and without being forced to strike uncontrolled during course changes or accelerations.

One Transport or container ship would be z. B. with at least 4 snap hook winches, which are mounted at a distance of 90 degrees to the inner ring, equipped.

The first winch 5.2 left above has only a rope, or a belt that / must be attached to the cargo externally by robots or astronauts. The next winch on the top right is equipped with a ring at the end of the rope or belt, which usually also have to be placed by astronauts / robots.

at the winch at the bottom right is a snap hook, its closing part in this case not on the side, but opens up. Thought is here mainly to picking up outer space transport containers or corresponding thereto Provided brackets for attaching the hook.

These possibility simple (even robotic) load handling and attachment is one of the main advantages of such with external drive and Docking cargo inner ring equipped solar glider / spacecraft across from the giant, square mast solar gliders for cargo transportation, the used in the previous solar sailer designs. The inventor / author can not imagine how the recording, or the dismissal of charge in such a huge mast sailer should be without that the spacecraft is endangered by the cargo especially due to risk of breakage of the mast bearing or risk of damaging the mast Solar sail.

Also if these problems may be due to appropriate navigation and Could master the movement of the spacecraft, would require the necessary Logistics, especially when operated from a distance Spacecraft make the handling only unnecessarily difficult.

The named clamping possibility is also for other reasons not to underestimate. So z. For example, the US company Orbital Recovery has developed a concept, Satellites whose fuel supply is ending and their orbit more and more approaching the earth, to move to a more remote orbit (GLES (TM) - Geosynch Spacecraft Life Extension System).

This could According to statements by Orbital Recovery the average lifespan of a satellite from 15 years to 25 years, which is not insignificant costs for Making and launching a satellite a significant cost savings would mean.

For this was an ion thruster engineered spacecraft constructed for the obvious according to internet pages of the company still a patent application is pending.

This vehicle should be attached to the satellite to be towed, this with the help of the ion-An haul the drive on the intended orbit and continue to remain attached until the end of the period of use of this as a replacement drive unit.

The link-up However, according to experts according to NewScientist.com is not just safe, a little push could do that Turn the satellite in such a way that it rotates uncontrollably. The towing vehicle, which is not provided with a holding option, would be in one helpless and the mission failed.

One Drive ring spacecraft with docking ring would be at a similar Use at least simplify the coupling, since the clamping of a Satellites from several sides by means of rope winches attached to the ring possible would be and However, a robot still to be developed on the service unit better deal with a critical situation with his four arms could.

Another possibility would be to provide the towing vehicle with flyable holding (in particular electromagnet) or gripping devices which are attached to the ends of the cables / straps of the winches. In 8th this is through the winch unit 5.2 shown lower left.

It this is again a smaller flying ring, the type already discussed in the pre-proposal. Such a flying ring could z. B. also help an astronaut to a desired To get to the place of use. It is easy by pulling the winch pulled on the inner ring and there possibly still supported by Electric magnet holder held on the ring until it is used comes.

The The simplest type of coupling seems to be the electromagnetic. Therefore, it is useful if the winch flying unit with a switchable Electromagnet and the transported material itself magnetic or at least with magnetic coupling surfaces, the at the for this best Bodies are attached, equipped.

Of the Coupling process then takes place by approaching the winch flying units to the cargo, switching on the electromagnet and contact. By tightening the winches to the desired transport voltage is the cargo then during the transport held in the inner ring. Then it can then dismiss or even first be transported by the winch flying units to their destination (if it is in outer space).

Of the Inventors assume that when using ion thrusters on the flying rings of the winch flying units neither damage to transported goods still arises at space transport vehicle, because in contrast to chemical Drives only charged parts (eg from xenon gas) instead of ignited Fuel ejected become.

When Material for I propose the ropes / thread / straps of the winches, this carbon Nanotube (CNT) materials are being used already today (eg by the French Company Nanoledge) are manufactured industrially.

This Material is incredibly tear-resistant, Space suitable and also still electrically conductive. So z. B. with a CNT thread of sewing thread strength Earth's a car will be kept in the air (source Edwards / Westling "The Space Elevator ").

This is natural in space (and on gravitational asteroids) perfectly adequate, Since no gravity is to be overcome in space, so draw such a "string" objects or could hold which would weigh thousands of tons on earth.

moreover comes the electrical conductivity just right, for the to conduct the electromagnet required current. So z. B. generates a verzwirnter thread from at least two CNT strands of which at least one or possibly both are electrically are isolated so that the required positive and negative voltage across the Threads from the Spaceship is led to the electromagnets of the winch flying units.

Replacement of the straps and straps 2.1 . 2.2 and 2.3 by highly tear-resistant "threads" in the form of a covering

Not only (but also) the above-mentioned enormous resistance of the Nanotube material, but also the expected low mechanical loads, have caused the developer to be his original reconsider the concept of the belt fastenings in the thruster ring.

The Belts have their advantages, eg. B. an unimaginable durability, the usability of proven belt fastening technologies (Ratchets, tensioners, etc.) and also the chance of having a strap itself is not completely destroyed by micro-meteors, because few of them Meteors a larger diameter than 2 cm (The Space Elevator, page 27).

nanotubes have a theoretical maximum tensile strength of 3000 tons each Square centimeter (The Space Elevator page 9), this corresponds a 1 mm thick belt of 10 cm width.

Of course, this theoretical strength can not (yet) be achieved, but the authors of this non-fiction book calculate for the cable of their Space Elevator with at least 1327 tons load capacity per cm ² strength.

is it except, however in the case of fast-rotating structures such as those dealt with in the pre-proposal Rotary spinner absolutely necessary, to demand such a durability in space? And this in one Environment in the tons of masses no, or hardly a weight or in free-fall condition and regular loading the structure moreover even by the low acceleration capacity of the solar sails used and ion thruster drives is limited.

For a research spaceship, that exclusively is used in space and only the required scientific Instruments and solar cell systems for power generation as payload promoted certainly not.

As that would be Whole look at a lander landing on an asteroid and there gains and removes raw materials? We take as an example a larger asteroid or the Marsmond Phobos the z. B. one for a minor planet already quite respectable gravity of one-thousandth of the earthly Gravity developed.

A and extracted from the asteroid raw material amount of An earth bin would have one Asteroid weight of only one kg ..

Even a "normal" carbon fiber twine of 1 mm ² thickness (with a possible tensile load of 210 tons per square centimeter, so 2.10 to per qmm) would be hopelessly oversized to keep this load at a start.

The Idea is therefore the design of the head of a badminton racket to transmit the here treated spacecraft with thruster ring.

The is called, the thruster ring would receive a net-like covering with intersecting (ideally crossing at right angles) threads.

The Tension of these threads would one relatively rigid area leave on the almost arbitrary at all points of the plane, payload can be fastened (eg by simple tying and knotting, but also using appropriate fittings, such as z. B. gripping hook).

In usually would this is done in such a way, the solar sail and solar cells on the one mostly the sun-facing side are fixed while the remaining payload housed on the underside of the fabric is.

Indeed would be the Frame in this case the ideally regular round thruster ring. By the Tube of this ring would have Completely through both walls through holes, which are slightly wider than the diameter of the thread, be drilled.

Of the Thread each at one end a thickening or a knot and would at the outer hole the outer pipe wall threaded, through the parallel hole on the inner side of the pipe wall as well passed and on the other side of the ring, first through the inner tube wall and then through the outer tube wall outward pulled and knotted there Ideally tense.

The separate knotting of each thread would be even with the destruction of individual threads By meteorite impact continues to give a certain strength of the structure, as long as the outer ring is also damaged.

Also in the stringing technique could on experience in the covering of badminton rackets by using similar ones equipment and techniques are used become.

So it has proven itself first all clamp in parallel tendons and then the intersecting Tendons seen from above alternately below then over the next and then again under the second tendon thread through, etc. resulting in a reinforcing on all sides string, the occurring point loads to a large extent on the overall structure derived and distributed.

Which Sense now has the use of threads instead of in the pre-proposal proposed straps to produce the required carrying and Support structure for payload attachment?

By the use of threads can the total weight of such a support structure again be significantly reduced, especially when it comes to larger units is.

Fewer Weight of the basic structure while maintaining functionality means but a higher one Acceleration, and thereby a higher final speed same available standing acceleration force and / or the possibility of additional Carry payload to be able to.

Just z. As in solar gliders, which manage with very low acceleration forces Everybody counts especially kilograms saved.

So z. For example, a 100 meter long belt of 1 mm thickness and a width of 2 cm (0.001 m ³ ) alone has a weight of 4 kg when using graphite fibers and an earth weight of 2.6 kg when using CNT material ,

However, a 100 m long strand of 0.5 mm ² thickness (50 cm ³ ) would only have a weight of about 100 g for graphite and 65 g for nanotube material (density Graphite 2.0 G / cm ³ , density CNT 1 , 3 G / cm ³ ) and would still be significantly oversized for use in gravity-free space and on low-gravity asteroids, as the CNT thread could still carry 6,635 tons of material that was not needed.

Even if the number of threads used by the stringing technique in relation to a Gurtbestückung yet clearly increased would, could still total weight saved in a further reduction of the thread thickness although at the same time the occurring loads are better distributed are and the mounting options through the higher Number of threads increase.

Even though through the o. a. Stringing technology already a very light spacecraft structure with high stability at the same time possible is, there are other optimization options available by the tube cross sections still further to that actually with certain Einsatzformen expected loads reduced and the number of threads on actually needed Number for safe maintenance of the payload is reduced.

so optimized spacecraft structures in which all unnecessary structural parts is omitted and only there mass is used, where to preserve stability and for the attachment of payload is actually needed allow especially in vehicles, mainly for locomotion without payload transport provided to a greater extent are, a significant increase in speed.

This may well with the increase the effectiveness Data storage in the computer area compared by compression become.

ferromagnetic Mounting brackets as fastening holders on straps

Even though for "normal" spacecraft the payload attachment the above Halteetz- or stringing method because of the lower mass in most cases certainly the better Be solution likely, also has the Gurtbefestigungs-process z. Eg with huge objects his entitlement continues.

Wide strips of ferromagnetic material could be placed exactly in the desired places on the fastening and holding straps of the holding net and would make it possible to ma objects to attach it to it.

The Attachment would by simply pressing with a crimping tool. A conceivable one Field of application would be z. As the attachment of solar cells to the tethers of a large solar power space power plant.

(Private) economic Application options

While the recent developments in space science though scientific and technological advances also in other areas except for the use of satellites for television broadcasting. and messaging, also for military Applications first once scarcely applications developed, with which for profit aligned Business enterprises could make money, if not easy Space products for public Produce client.

For the space industry and advancement of space travel there is always the danger that The taxpayer is no longer willing to pay the enormous sums of money same height continue to pay as before.

Especially this applies z. B. crashes of spacecraft and death of astronauts, as well as in war and War danger and the associated higher capital requirement but also easy in economic downturns and thus more scarce Financial resources.

Around an economic disaster for to avoid the companies concerned and their employees, There is therefore an urgent need for new fields of activity for the space industry to open up which promise a profit in the foreseeable future.

It But it is also necessary, the horrendous cost of individual Reduce missions, through the use of reusable spacecraft, who stay stationed in the room (like the solar sailors presented here) as well as the fuel-saving solar sail technology and here also presented modularization in the opinion of the inventor quite possible would.

The Mother ships developed here do not always have to be new Can be catapulted into space and can for many different missions Find application.

she can refueled by replacing the thruster units and to the latest Thruster techniques are modernized.

For the implementation of special Missions are only the daughter units (which are mostly reusable are) to reschedule, manufacture and move into space, though already reusable mother ships are available.

hereby could on the one hand, the production costs attributable to a single mission for the used Spacecraft and on the other the fuel and technology effort to overcome the high hurdle minimizes the earth's gravity and when using solar gliders in terms of fuel consumption can be further reduced.

ever less fuel has to be transported, the more power remains for the payload or the lower the turnaround for the spacecraft, thus correspondingly weaker (and thus cheaper) can be designed.

One conceivable economic field of activity for the presented technology would be Therefore, finding, recovering and processing raw materials in the Space.

Find, Win and Processing of raw materials in space.

Of the most promising short term feasible approach to extraterrestrial Extraction of raw materials is not in the colonization of the moon or of Mars by humans (in particular also because of the effort to Provide life-sustaining systems and because of the prevailing there relatively high gravity), but in the robotic extraction of raw materials of asteroids and comets, as far as possible close to the sun should.

These Small planet have a very slight gravity, so that it for the Thrusterring solar sailor with the help of usually for The control thruster used is possible over these floating samples and if necessary even to land and afterwards ascend again or carry this through the entrained lander to to let.

Something, what all previously conceived solar sail models in the opinion of the inventor can not afford.

Either the considerably lower density of the soil due to microgravity and thus easier conveyance as well as the quality the raw materials speaks for the extraction of raw materials from asteroids.

at the heavier heavenly bodies like moons and planets are the heavy and precious metals because of gravity, for the most part in deeper, not more achievable areas have dropped, while the smallest planets the promotion almost on the surface possible is.

conventional Spacecraft with chemical drive would be for such use rather unsuitable, since they would be able to do one if they were able to do so To reach asteroids at its location with the available fuel, Would have problems also to land there, to ascend again and to return to earth.

The Exploitation of possible solar asteroid is so favorable because the driving force of the Solar sails when halving the distance to the sun square increases (at 0.25 AU, so a quarter of the Earth's solar range from the sun is the solar radiation acting on the sail 16 times as strong as at ground level) and also the for the ion thruster operation required solar radiation on the solar cells act.

Either the sail area and thus the size of the sailor as well as the solar collectors can therefore at an approximation be designed to the sun considerably smaller.

Even though Solar sail presumably also on its own power over asteroids can float, is a better maneuverability at exclusively thruster-powered vehicles.

The presented here option the use of spacecraft combinations, consisting of the with a solar sailed mothership and a lander, whose Drive ring exclusively provided with a thruster drive (in particular ion drive), is therefore a good alternative.

in this connection land or hover only the dockable, low-mass land units, on / above the Minor planet while the great and faster mothership for the actual transport is responsible.

This Lander could equipped with a parachute be that from the outset at the top of its drive ring would be attached in unfolded state.

To the return transport by the mother sailor in the earth orbit then he could then a second time from Disconnect the mothership and with the help of the parachute on the ground land. Should he survive this undamaged, would one Reuse after replacing the thruster also nothing in the Stand ways.

Is that claimed by the inventor landing capability on, or Schwebefähigkeit over a Including asteroids Arrival and return Realistic with low accelerating thrusters?

The an ion engine quite larger and can drive heavier structures as the main propulsion, shows the Smart I spacecraft of the ESA. The 75 milli-Newton drive (7.5 grams of thrust per second) manages the orbit of the 367 kg (of which 80 kg Fuel) heavy missile to increase the earth ever further, so that he finally to get into a lunar orbit.

Expected comes with a 2 to 2.5 year mission, during the the engine works almost continuously.

The Smart I engine would be however, when using multiple thrusters on a drive ring because of the excessive weight and the oversize oversized and not practical.

When example for use on a thruster-ring vehicle could be the Russian SPT-60 engine, that since 1971 in space for the correction of satellite orbits is used, apply.

It has a driving force of 30 mN and weighs 1.2 kg. Source http://www.videocosmos.com/magazine/nk0799.html

As with the design after 1 drive at least 4 thrusters in one direction, would reach 120 mN drive, so in total but significantly more than the Smart I drive with its 75 mN.

Would not be the limited fuel capacity, could this spacecraft thus at the same weight as Smart I the moon or even near-Earth asteroids (Near Earth Asteroids - NEAs) - possibly from its own Achieve power without having to use the solar sail for this purpose.

By the extreme lightweight construction and because of the associated lower Weight over Smart I could However, this is much faster than this.

The total weight of the 12 double thruster units after 1 with a total of 24 thrusters, at least 24 x 1.3 kg (1200g thruster weight and about 100g of surrounding tube) would weigh 31.2kg.

In contrast to the 80 kg fuel needed for Smart I per double thruster unit (see 2.a to 2.d ) However, only about 600 grams of fuel carried, so a total of only 7.2 kg.

The Total weight of the carried Including ion drives Fuel would in such a case thus under 40 kg make up.

One Solar sailor with such a decorated thruster ring would be however able to last much longer than Smart I to be used with acceleration, since the main drive not with the thrusters but with the sail and the thrusters only needed Be the spacecraft in the desired location to the driving To turn solar radiation.

It thus much less fuel must be carried.

Watch Let's look at the driving force of a round solar sail from about 100 m in diameter.

On Erdhöhe develops a solar sail the size of a square kilometer about 9 Newton drive. Converted to the smaller 100-m sail this would be about 70 mN, so slightly less than the main propulsion of Smart I.

This would be like that Enough around the (lighter) solar sail spacecraft just like Slowly push Smart I out of Earth orbit into outer space. The further it approaches the sun, the stronger it rises however, the performance of the sail.

What mass would have z. B. a 100-m mother-sailor with 5-m lander?

It here's just a rough estimate for the carrying structure, as well as solar sails and thrusters with fuel for a 100 m mother ship to be made with a 5 m lander. Regarding scientific and other payload as well as solar collectors will try on one estimate waived.

at the mothership is a solar glider with 12 double tube units, a 100-m outer ring and a 5.5 m inner ring of CNT tube material with a diameter of 6 cm and a wall thickness of 1 mm.

Of the outer ring is provided inside with a fabric of 0.5 mm CNT threads, which is set at a distance of 25 cm and the inner ring in the Center of the spacecraft stops.

Mother sailer (with 6cm outer ring, inner ring, holding net thread distance 25 cm)

Lander (without solar sail with 6 cm outer ring, holding net thread distance 10 cm)

at The lander became Russian SPT-50 thrusters with 20 mN thrust, a weight of 800 g and about 300 g of fuel per double thruster unit based on.

The low weight of the basic structure of the lander of 16.4 kg seems to be out of proportion, with the almost wasteful space of almost 20 m ² , which also still on both sides, ie above and below the holding net is available.

expects about 120 kg for Solar cells and other payloads would add mothership and lander together are in the weight class of Smart I, but significantly exceed its functionality and application.

Landing on, or hovering over one asteroids

At the 12.02.2001 landed the ion-thruster-driven NASA NEAR- (Near Earth asteroid rendezvous) Shoemaker undamaged on the asteroid Eros, although she does not even have this was constructed.

in the Considering that Eros is one of the largest near-Earth asteroids with corresponding to "high" gravity, obviously it does not seem that hard on an asteroid to land.

Indeed In this case, a control program is required, which the lander allows you to make your own decisions and control them automatically, because a remote control is likely because of the time delay illusory be.

As But is it about starting or hovering over an asteroid? Can they weak ion drives master such loads at all? We take as an example, once the lander treated above, with payload including The materials recovered from the asteroid are assumed to be recycled Earth weight of 100 kg should have.

The Average Gravity on Eros is about 0.6 per thousand of Earth's gravity.

Of the loaded landers would have on Eros thus only a weight of 60 grams. If now the four Russian thrusters described in the previous example with theirs 20 mN, so a total of 80 mN (this corresponds to about 8 grams) the lander would drive During she will not be able to lift this from Eros.

Now Eros, however, has the quite impressive dimensions of 34 times 13 times 13 kilometers.

Different see the However, bill for considerably smaller asteroids, z. B. at Asteroids with a diameter of about 1 km or only a few a hundred meters. Here would be quite a resurgence of the lander with the help of such weak ones Ion thruster possible.

So is currently Japanese accelerated by four ion engines Spacecraft Muses-C, or Hayabusa called, on the way to Asteroids 25314 Itokowa. This asteroid has an estimated size of 490 times 180 m and an estimated Gravity of one 750 thousandth of Earth's gravity.

This means, the o. a. 100 kg lander would have an asteroid weight in this case of only 0.13 grams! The 8 grams of thrust donating ion drive our example above would be thus considerably oversized.

So obviously the Japanese also assume that this asteroid also for Landings of ion-propelled vehicles is suitable for it is provided, the Japanese spacecraft, the asteroid in July 2005, hovering over both the asteroid to let as well as two to three times to land on this around there Take samples and then start again and the samples for To bring back earth.

The Japanese just watch the sampling because of the extremely low Gravity as big Challenge. You want a projectile with a small one firing pyrotechnic charge into the asteroid surface, with the part being a part the surface destroyed should be around afterwards to capture the flying impact fragments in a sample container. (Source: http://www.spacedaily.com/news/japan-muses-c-04a.html) Stop them therefor a thruster-ring spacecraft of the type described here would be available considerably easier, because it could with the help of the upward thruster a counter pressure directed against the asteroid surface exercise and even perform drilling drills without fear that the spacecraft would pushed away from the asteroid.

The However, presented thruster ring design is not exclusive to instructed electrical thruster. So z. For example, the European nanosatellite SNAP I of the Surrey Space Center equipped with butane liquefied gas tubes, the including Fuel supply and "tank space" (the fuel is housed in the fuel lines) only 450 g in weight hit and drive each 100 mN drive.

It might certainly not a problem, especially for the lander on a performance from Z. B.

250 mN (with 4 thrusters 4 × 250 mN = 1 N = 100 grams) Miniature drives of this kind produce, which then again a Start from the gravitational stronger Asteroids Eros would be trouble-free.

This "cold gas thruster " across from the advantage of higher power at lower ion drives Weight and also the lower power requirement, so smaller Solar cells needed which in turn reduces weight again.

adversely is then, however, the lower effectiveness and by the exiting burning gases caused danger of the mothership when docking. However, since the Thrusterringfahrzeuge certainly can accommodate several thruster species on the ring is also in addition to Ion drive the use of cold gas thrusters for asteroid starts possible.

Collect / Win Asteroid material

Next Of course, the electromagnets preferred by the inventor are also even more holding devices such. B. retaining rings, snap hook, etc., which for Different purposes may have their meaning, possible and conceivable.

in this connection in particular still on robotic arms, or gripping and excavator similar Pointed gripping devices.

So z. As a solar glider or spacecraft float with thruster ring over an asteroid and there by means of winch-Flugringe 5.2 to 8th and gripping and collecting devices attached thereto from the asteroid surface to collect rock, ore, dust, and sand-like resources.

Also the lander of the above example could be at the winches by means of CNT yarns from the mothership, which is z. B. 200 m above this, down to be left. Advantage of this procedure is that when dusty substrates no dust cloud would be whirled up, which no longer lays because of the low gravity.

So is located z. For example, on the Marsmond Phobos a meter-thick layer of dust; This is certainly to be expected with some asteroids.

Of the Lander would only use its side and upward ejecting drives. The lifting off of the underground could by tightening the winches or moving through the far-off Mother ship done so that the stirring up of dust here is avoided.

The Suspend and carry Land vehicles with wheel or other mechanical drive not only because of the dust load on asteroids with less Gravity no longer makes sense.

Z. B. could an earth-heavy excavator on earth (apart from the missing one) Traction for the propulsion) solely by using his shovel in the universe or at least put into orbit if it is not in any way Form is attached to the ground.

The The most sensible method of locomotion on asteroids is therefore flying or hovering.

in the Unlike ground vehicles are the Thruster Ring spacecraft discussed here for winning of asteroid minerals ideal, because they can not only free about the surface to almost any desired Move place, but also if necessary, you can also control these from your own power from outer space and the recovered material to possibly distant destination (eg to earth).

As well is the orientation of the thruster-driving units, both after can accelerate up as well as down, suitable for the missing, normally pressure generated by gravity due to its thrust to create.

In addition, the Thrusterringfahrzeuge in addition to the pressure down also a rotary motion, the by attaching the thruster to the outside by a very long Lever reinforced will, exercise and thus screw anchor u. ä. screw into the ground.

The Thruster ring spacecraft or parent / subsidiary combinations presented herewith are therefore, in my opinion in connection with a solar gel and the inner ring as well as the winches with flying rings particularly suitable for asteroid material of the surface of asteroids appropriate and economical to win and transport, since this hardly requires fuel.

Use of the inner ring in cargo ships as cargo and cargo handling unit

One Solar sailor of the kind treated here can of course and especially used as a cargo ship. Here comes the great Advantage of the solar sail, the largely free transport through Use of freely available Full use of solar energy.

A especially cheap Configuration would be in the opinion of the inventor, the use of a single flyable payload platform or payload container that does not use a solar sail itself, however, using an outer ring flyable with Steckthrustereinheiten and is capable of docking on the solar sail mothership dock or drop off and then the destination with independently to achieve your own strength.

The Accommodation of cargo in the center is particularly important, as a result the controllability favors becomes.

So z. B. replenishment to a space station or a minor planet by means of a payload platform In return, the returning solar sailor exchanges a second platform already loaded with the raw materials extracted there, which then at the destination (eg a near-earth space station) against another already loaded replenishment Payload platform is exchanged.

Booster as capable of coupling Function unit for accelerating a spacecraft with inner ring

A conceivable functional unit for coupling in the inner ring of a drive ring spacecraft z. B. a converted booster unit of a launcher. This would z. B. with a launcher Instead of two, four booster carried, of which only two ignited at the launch would.

The both unused booster would then stand for acceleration the thruster ring spacecraft to disposal.

In this case would the drive-ring spacecraft approach the booster and this then in the inner ring lashed by straps. These would be appropriate handles provided around the middle part of the booster.

After this ignited the booster and burned out, could he then separated while the drive ring spacecraft continues to accelerate.

By this procedure could thus the greater thrust and high initial acceleration of the chemical drives also for the thruster ring space vehicles be used.

double Inner ring as a double docking device

It is a pity, the precious space in the center of a spacecraft to waste. A possible solution is, the opening in the disc by two correspondingly spaced superimposed coupling rings double use and the coupling or loading from both sides of the spacecraft.

In 8.a such a double inner ring unit is shown. As a rule, exclusively ion-thruster-controlled vehicles should be coupled in so that the second vehicle coupled on the opposite side is not damaged.

Magazine Dock inner ring for coupling several daughter-ring spacecraft

8th Fig. b shows an inner ring docking and loading unit which allows a larger number of thruster ring spacecraft to be picked up and decoupled.

• a) Transport und Platzierung ganzer Satellitenschwärme, z. B. zur Sonnen- und Planetenbeobachtung oder auch als Kommunikationssatelliten. So könnten z. B. Mars und/oder Mond schnell flächendeckend mit Kommunikationssatelliten ausgerüstet werden, was eine ähnliche Kommunikations-Struktur wie auf der Erde (bis auf die Zeitverzögerung) ermöglichen würde.
• b) Transport mehrerer unterschiedliche ausgerüsteter Tochtereinheiten, z. B. um Asteroiden-Rohstoffe mit verschiedenen Gerätschaften abzubauen.
• c) Transport mehrerer Container-Einheiten durch ein Container-Frachtschiff.
• d) Transport mehrerer Innenring-Flug- und Stromversorgungseinheiten, durch ein Werkstatt-Mutterschiff, das darauf spezialisiert ist, diese Einheiten an bewegungsunfähigen Satelliten zu befestigen, bzw. diese mit Strom zu versorgen.

U. a. the following applications are conceivable:

• a) Transport and placement of whole satellite swarms, z. B. for solar and planetary observation or as communication satellites. So z. For example, Mars and / or the Moon can be rapidly equipped with communications satellites, which would allow a communication structure similar to that on Earth (except for the time delay).
• b) Transport of several different equipped daughter units, eg. B. to reduce asteroid raw materials with different equipment.
• c) Transport of several container units by a container cargo ship.
• d) Transportation of multiple inner ring flight and power units, by a workshop mother ship specialized in powering these units to powered satellites.

In The drawing is a preferred embodiment with a center ring shown. At this middle ring are on both sides four pipes at equal intervals attached to the torus body Seen from vertically up and down and stand at the In turn, two torus rings are attached to the other end.

These Konstuktion thus represents an open at both ends, cylindrical pipe skeleton, that makes it possible to stack several daughter units in its interior, so to speak.

The locking of the daughter ships in the framework takes place in this case by projecting into the frame Rack mountings which can be moved into and out of the docking room by means of electric motors and worm threads.

The Attachment function is additional still supported by electromagnetic brackets at the contact points of the rack mountings.

Mobile Solar Cell Space Kraükwerk (Solar Power Station - SPS)

With US Patent 6,194,790 B1 dated 27.02.2001 has become a) space-based (s) Solar power station / solar power extraction station based on a Solar sailgels, whose sailcloth with a photovoltaic power generating Coating is provided, patented.

in this connection The solar sail properties are not for locomotion, but used for alignment, deployment and stiffening of the structure.

The actual movement function of the sail is rather undesirable and must with Help of thrusters that the abortive awning again towards Move the sun, or it at the same height against the radiation pressure hold, be balanced.

There it is a self-unfolding structure, it is obvious that applicability is currently limited to smaller units in the near-Earth Limited space is.

The The present invention deals with larger solar power plants space-assemblable thruster-ring constructions with suspended power-generating Sailing or solar cell cluster units passing through the thruster rings and possibly the sail in addition are able to change their location, and like a spacecraft to navigate or a distant location on their own to reach.

Can z. B. Ion thruster driving a massive PLC? Considering that the efficiency of the ion thrusters with the available electrical Energy is rising and this is just enough for a power plant Measure to disposal stands, one can only affirm this question.

Finally is the number of usable thrusters is not limited. A power plant in the square kilometer area could on its outer ring record hundreds of thrusters.

So has been recently from NASA announced that the newly developed HIPEP internal drive with ejection speeds from 60 km / sec. was operated, which is a doubling of the previous possible ejection speeds means.

The Moving a power plant in the manner of a spacecraft should Therefore, be possible only with the help of a sufficient assembly with ion drives.

By the combination with an inner ring as a docking station is also the Rapid replacement of functional units possible, so the power plant could functional units with laser transmission against a microwave transmitting unit or against a "flying Socket "or other power-consuming functional units, so to speak, in flight replace existing functional units with more modern ones.

Such a combination of a solar-oriented power plant with a target-oriented transmission unit is in 10 shown.

The Orientation of the power plant to the sun is similar to the orientation of a solar sail. By turning the power plant the drift generated by the radiation of the sun can be compensated, by turning it alternately so that it approaches the sun and Then it is turned again so that it is removed and thus a middle position can be maintained.

So could such a space-based power plant in near-Earth space (Near Earth orbit - NEO) mounted and then remotely controlled by the radiation belts of the Earth control its location (such as an asteroid) and there the necessary energy for provide the extraction and processing of asteroid precursors.

Now there are different ways to bring the energy to the end user. Once through the rays with the help of microwaves or as laser beams and on the other by direct connection of the consumer with the producer a (two-core) power cable. The energy rays in particular has the Advantage of better mobility. Transmitter and consumer are not limited by the power cables in their mobility.

Of the Disadvantage, however, is that any energy conversion and also the radiance over long distances significant losses.

So count Edwards / Westling in their book "The Space Elevator" for the supply the platform of their space elevator using laser transmission with an efficiency of only 3 to 14%, in the transfer by microwave radiation even only 0.05 (page 66, table 4.1).

Yet they prefer for the power supply of the actual space elevator, so to speak the Elevator cabin (climber), which rises by engine power at the elevator "rope", in the end a radiation solution, because, in their opinion, the loss of the line is over a hundred thousand kilometers Power line is horrendous and additional Significant danger of short circuit in case of possibly unavoidable contact the power lines over this size Distance could exist.

there the current should then be transferred from the laser Focus a 12-m mirror from Earth to the climber.

Indeed is at this solution very unsatisfactory, that the power to operate the laser on earth is generated and at the socket to the power consumer (laser) already significant losses have occurred.

A cleaner solution also for the environmental impact of the earth, would be it, the electricity for to generate the station through a space-based solar power plant and thus to avoid the burden of the earth's environment and the blasting the energy does not carry up from the earth to the climber, but down from the SPS to the climber.

10 shows such a power plant, which is basically a thruster ring spacecraft equipped with plenty of solar cell arrays and or a power sail, as well as with an inner ring 8th provided and adapted in size to the expected power consumption.

At the Inner rings are attached to winches, which at the same time as a power cable serving train cable in the center of an airborne laser / reflector functional unit with a flying ring. By the possibility both vehicles (though over the cables connected) separately from each other, they can be aligned separately to their goals.

The Power plant is thus usually geared to the sun while the Laser unit points to the power consumers to be supplied.

These Type of power transmission is certainly useful in the space elevator. However you could do that Conversion losses that arise because the generated Electricity over The laser is first converted into light and then the light again via solar cells converted back into electricity must become, at shorter distances by passing the current over Avoid power cable.

So could z. B. instead of the laser unit a daughter ship, which in principle acts as a flying outlet, used when obvious Places need to be powered. This is intended to be used over an asteroid, in which the power supply floats just a few hundred feet above the minor planet surface and the power over a cable to the "socket unit" at the place of use on or above the asteroid surface supplies.

Such a constellation is in 11 shown.

Solar power plants Additionally the energy supply of the earth

The transmission of energy by microwave radiation, despite the high conversion losses through conversion their purpose, namely to sen power from solar power plants (SPS) to sen the. The transmitted energy does not have to be generated by burning fossil substances on the earth and this contributes to environmental relief.

Otherwise it acts the "losses" are solar energy, which would also flow without PLC and does not have to be produced using raw materials.

The Power transmission via laser is more effective, but also more dangerous.

you must not overlook that such a space-based large power plant connected to a laser a very powerful one and dangerous Weapon is.

It would be like that desirable, if such power plants for the supply of the earth not at all be equipped with a laser but a microwave unit. These are not on a small spot but on receiving systems, their area in the square kilometer range, directed.

Different As with the microwave oven is not everything that is between the radiation source and end point is, cooked, but there is only one possibly. even desirable slight warming the environment instead of the radiation in the receiving unit (rectenna) is converted back into usable electricity.

Solar power plants for Melting and heating

After this the thruster ring PLC already equipped with a laser unit that can be over should have a virtually free energy supply on a gigantic scale also other uses in the eye become.

To heard this especially the use for heating and melting of asteroid or moon ores, to gain or process metals or sand / rocky Melting materials to glass, but also for targeted heating around chemical processes or setting processes as they are known, for. B, when concreting, that at least one temperature over Frost height needed to enable.

At the Switch from heating to heating just have to the laser melting functional unit decoupled and the otherwise focused, also laser-based Heat-functional unit be coupled.

considered you look that steelworks earlier often not close the ore mines, but rather located near coal mines were because in steel extraction enormous amounts of coal to molten steel necessary you realize how important this almost unlimited, free Energy supply is.

With The mobile thruster ring PLC also makes it possible to generate energy in the vicinity from suspected huge resource sources on asteroids and moons to bring and thus the environmental pollution of the earth by raw material extraction and to relieve processing. As well as the transport of these raw materials to the earth when using solar gliders would be cost-effective, could be the extraction and simultaneous Basic processing (melting) of such substances may also be economical be when this work is done by robotic functional units.

So could a cargo ship the container functional unit already treated elsewhere, their flying ring with a parachute spanned from the beginning is provided with the already pre-processed by melting raw materials throw off in the direction of the earth.

Thrusterring spacecraft as a mirror or lens

at the recovery / processing methods described above of raw materials by melting / heating with laser use is the Energy loss through conversion relatively high.

advantage the laser is in particular the possible exact bundling and alignment of the laser beam.

However, a bundling that is not quite as exact, but not always required to such an extent, is also possible when using a thruster ring space equipped with mirrors or lenses vehicle possible, with the conversion losses are avoided.

in this connection become mirrors on the risers or nets of the spacecraft or at a smaller scale also lenses attached to the desired distance and the desired one Scope of focus are focused. Then the vehicle placed in the working position and directs the beam to the in Focal point lying objects / Matertalien.

conceivable Use would be z. B. heating (especially the sides facing away from the sun) of concrete forms in which fittings to the frost-free heat levels required for concreteing being held.

Thrusterring spacecraft as mobile receiving and transmitting units

Of course it is also the attachment of huge bowl and antennas receiving and transmitters on the tethers / holding net of the thruster ring vehicles possible, which thereby become mobile space transmitters and receivers.

Screw and pluggable complete thruster units

A Further developing the idea of pluggable complete thruster units according to claim 8) of the pre-proposal, the screwdriving and pluggable complete-thruster units for Installation on small planets or the subsequently treated concrete spacecraft, Space stations and habitats.

Because of possibly threat to the earth through collisions with asteroids or comets were often considerations employed with the distraction of such a space body of to deal with his collision course.

Also the redirecting of such bodies in a near-earth orbit to z. For example, the resources available to exploit the minor planet better is always being considered.

one this thought, by the American Space Studies Institute (SSI) to the public was brought, sees the use of electromagnetic slingshot in the form of magnetic rails (rail guns) that are magnetic Material (eg ores) into space and thus the recoil principle the rockets for locomotion or orbit change of a minor planet to be able to use.

The Invention presented here is based on the idea of a minor planet to make it a spaceship, the drive units in the surface screwed in, or in prepared pods melted into the surface are to be plugged in.

advantage across from the SSI mass driver solution is that fuels are abundantly available in a space environment are the limitation on magnetic substances is avoided and not least a pollution the space environment by flying massdriver missiles, the long-term danger lead the space travel could, not taking place.

In 12 becomes a screwable and in 12 b a pluggable thruster unit which is inserted into a retractable sleeve shown. These units can be filled from the outside with fuel, a refueling is therefore possible.

Around now to control a minor planet is this with a sufficient Provide number of thruster units at appropriate locations, which are controlled by remote control coordinated.

These solution is certainly the use of a "space tugs" so a tug preferable to sit carefully behind the minor planet and this pushes, especially if this "only" about one low-thrust internal drive features.

The However, screw-in thrust units can be used with higher-shear steam or chemical Drives where the fuel may be directly from the driven Asteroids can be obtained, operated.

They are provided with a fuel tank, which can be refilled via a filler neck and preferably have a receiving unit that allows remote control of the minor planet. For minor planet units, there is an additional power supply. 9 is intended to represent such a minor planet that can be controlled by multiple thruster units.

screw in of screw objects on small planets

One Problem is the "screwing in" the thruster in the minor planet underground. Conventional tillage equipment, such as z. As rammers, excavators, etc. are because of the lack or extremely low gravity can not be used, as they are in the appropriate application in the Space or into orbit around the minor planet could repel.

Because of they would also be more cautious of the lack of back pressure due to gravity Operation hardly able to attach solid substances by mechanical action to solve.

One Spacecraft with thruster ring after the pre-proposal already made could However, this lack of pressure of gravity means down oppressive Create thruster.

ion thruster would be though for one such task probably still too weak, so to others Small thruster types used must become.

For the generation However, the rotation for screwing the screw could quite ionthruster can be used, because this is an extremely greater Lever available stands (eg would at an outer ring diameter 10 m spacecraft each of 2 opposite side jet thrusters facing each other move a lever of about 5 m).

Also other objects, eg. As drilling anchors or drills, Claimmarkierungspfähle (provided with transmitters to mark the mining area of prospecting owners) can with the help of pressure-exerting Characteristics and the big one Levers are set during rotation through the ring spacecraft.

One Problem of this mounting option could the low density of the asteroid underground, so that already very weak forces sufficient to overturn the submerged thruster units or torn from their anchorage.

A possible solution would be that Setting screw sleeves and subsequent Melting of the surrounding substrates (eg to glass surfaces) by laser.

To Could cool the environment then the thruster units are inserted into the sleeves, the now by the solidified solid mass in the desired Location would be held.

Procedures and aids for the exploitation of raw materials on small planets of the rotary lever and thruster pressure of a thruster-ring spacecraft.

The first non-soil soil sample was made by the Russian lunar Luna 16 taken. In this case, a robot arm attached to the land probe was used to drill a downwardly open cylindrical sampling container into the ground. This also succeeded to a depth of about 30 cm, until resistance was hit. The soil sample remained through the internal pressure in the extraction cylinder without falling out again and could be transported back to earth with a return unit.

On The moon was supported by the moon gravity. One However, Kleinplanet has such a low gravity that one Sampling with the lander on this minor planet would not be possible because no back pressure is present. However, if you use a spacecraft with thruster ring according to the previous patent application, this can Back pressure applied again and the sample is taken with such a withdrawal cylinder.

By slow rotation of the spacecraft and with simultaneous application of pressure to down could it is also possible be to gain sand or gravel-like raw materials in larger quantities by this through a conveyor slot with downwardly dished scraper or cutting nose (similar to a Potato grater) in a large cylindrical container is pressed.

minor planets are the first choice for the extraction of resources in space, because not against the gravity of a big one Moon or planet fought would have to be and on the other hand valuable raw materials, those of higher-gravity ones Objects long ago immersed in the core there still on the surface to be funded in the open pit, so to speak would. Such raw materials are likely on minor planets in larger quantities to be found and could u. a. be used as a raw material for concreting which already the by volume the largest share the raw materials (sand, cement and water) needed for concreting, would be won.

Also the required water could in ice-containing asteroids by a with a corresponding functional unit equipped another spacecraft can be obtained (eg by evaporation).

pluggable Thrustereinheiten

A another possibility to use the pluggable thru unit, z. B. on spacecraft or so-called Space Habitats (space settlements) that protect against the dangerous Space radiation with meter-thick walls (eg made of concrete) provided are.

These huge wall thickness would it allow recesses for Thrust units including the required fuel from the outset in the preparation of the Outer wall elements and then place the units directly in the recesses or in addition sleeves, which fitted into the recess are to use.

The complete thruster units are then simply in the recess inserted and screwed from above on a protruding stop ring.

The "refueling" of the unit takes place in this case over a tank neck from above.

A Another variant is the fuel supply from below. Here is a lockable filling pipe Completely through the outer wall passed, and flows in an inner tank. Another tube, then into the Thrust unit opens, serves to supply them.

Use of the Rotary lever for Drill brackets and other screwing devices

Of the Rotary lever of the solar glider can also be used by Bohrhalterungen screw anchors, claw markers or screw extractor units on low-gravity minor planets (eg asteroids).

It this is located at the center of the thruster spacecraft holders adapted to their specific purpose.

outlook

To all the different inventions in this and the previous one Patent application would like to be treated I have a view over a possible future Development of space travel, as I wish, give.

there I assume that much of the evolution of space travel done robotically. As much as I can people as fast as possible want to experience on the moon or Mars, seems to me the most sensible and most promising approach, first of all the use of Robots to the fastest possible Building a space infrastructure and exploring ours Environment, ie the inner solar system from the sun to Mars.

robot (count this I also remote-controlled spacecraft) do not die and need no life support systems and environments; the transportable Payload is significantly reduced, the cost of further development Space travel is falling significantly.

At the Example of the American manned space flight, which after the under enormous financial efforts have been made since moon landing Already more than 3 decades nothing like this more accomplished has, (except Shoot people in a near-earth circular orbit and bring them back from there) we should learn.

Which Had benefits that Americans can accomplish, if you like the sums of money that burned in these about 35 years and the resulting manpower, fully contributing to the development of robotic space technology and infrastructure construction would have?

I suspect that they would already be able to raw materials, in particular To recover and process asteroid fuels, some the promising more effective, but weaker because less push-drive types and robotic control significantly further developed and over space-based robotic fleets would have the We already have a better, more comprehensive picture of that inner solar system could have procured.

On the other hand NASA is now richer in reality by the knowledge that the space shuttle too expensive a costly means of transport is because the Providing human habitat and life support systems, which, in addition to other payloads, have to be carried into space again and again.

The Concern for human life requires more elaborate measures, such as B. double and triple quality controls of components, to secure the success of the mission and thus human life simply necessary.

This hardly leaves still financial scope for other developments.

In spite of the high expenses astronauts had to die. Nevertheless, we have to watch today that the ISS only maintained an emergency operation can, because the Americans stopped their shuttle service once have and possibly even the danger exists that the operation set for financial reasons must become.

If already at a near-Earth company like the ISS there is a danger that politicians stop it for (not entirely unfounded) cost reasons, would this danger not all the more so in such a reckless, resource-eating Companies like a human Mars exploration?

If it already causes such problems, a human occupation for a long time to hold in a near-Earth orbit, then let the financial Expenses and the dangers for the astronauts justify this during a two-year journey by the harsh radiation exposure in open space beyond of the protective Earth's magnetic field and the health burden of bones and Muscle loss due to lack of gravity have to take on?

Even if not yet solved Problems of radiation exposure and lack of earth gravity solved and the Financing such a company with tremendous effort would be possible, then exist not after a done the successful mission of Mars the danger that afterwards for exhausted means over decades Nothing happens, as after the moon landing for decades no more is followed?

is it justified by the planting of a flag such means, the for the Development of other space technologies, with which possibly a direct economic benefits for the earth can be achieved, delaying decisively?

Which one direct economic benefit could be pulled out of a Mars landing if the cost overcomes the distance and the gravity prevailing there stay?

To my opinion should be first the robotic space travel, in particular for the extraction and processing of raw materials and energy (and thus avoidance of Combustion and transfer of harmful to the environment Production processes - eg. B. molten metal -) be further developed into space.

From this could create lasting structures that create jobs (also robotic systems need controlled, manufactured and developed), the environment of the earth relieve themselves and because of the enormous amounts expected on asteroids most valuable mineral resources in shorter Time as a Mars or lunar settlement also count economically.

This is economically most useful by the use of low-gravity minor planets in the sun proximity, in particular because of the rich energy supply and the possibility to transport by using solar gliders extremely cost-effective.

Around Do not make a false impression, I would like to emphasize that too I quite dream of another moon or Mars landing and I even thought about it do, how to achieve this goal.

I my only, it would be not smart to try the second step before the first because the danger is that well-intentioned, through wishful thinking, Adventurousness or exaggerated, misunderstood nationalism (our country was the first that ...) driven efforts due to unrealistic cost planning in an economic Dead end.

First if the infrastructure exists, which allows for the most part the necessary resources for To get such an adventure in space would be one Undertake m. E. meaningful and with the help of the previously obtained Knowledge also (inexpensive) possible.

Earliest time for the Beginning of a human spaceflight, beyond the sphere of action of the magnetic fields leading the earth out, should therefore, in my opinion the one to which we are capable, at least the fuel and possibly even the outer shell of the Spaceship from raw materials extracted in space.

Previously would be necessary tasks thus building a diverse deployable, reusable robotic fleet as well like the closer Investigation of the asteroids and other minor planets recoverable Raw materials, as well as the development of processes for in situ processing / production of metals, glass, concrete, CNT materials in cooperation of the transport and logistics services provided agencies / facilities with the respective raw material processing industries.

Exactly This aim, however presumptuous it may sound, should be present here Inventions / designs serve.

Desirable would be that the space agencies here their restraint give up and focus not only on space but actively support the development of such production processes, even If necessary, develop yourself, patent and the Wirkschaft (possibly against reasonable royalties) to accelerate the conquest of space.

such Key Technology Production Patents In the hands of space agencies would be the development of space travel especially because of the very harmful, restricting the effects of patent law, namely the possibility the restriction the use of key technology patents to the patentees.

Further important infrastructure facilities are repair assembly and Maintenance stations, in the near-earth area (this certainly counts at the beginning the ISS) that make it possible to maintain the fleet in the protection of the Earth's magnetic field and space structures, such as B. spacecraft, production or solar power plants assembled, which then controlled robotic under their own power get to their place of work, as well as mobile workshop / maintenance spaceships.

One with increasingly advanced robotic technology logical next step would be then the possibility, Such structure facilities and production facilities the area of protection of the geomagnetic field in the L1-Librationsraum of the Earth / Sun system.

It is an area between the sun and the earth, in the gravity of the sun and the earth and solar energy constantly without shadows is available for maintaining production processes.

From there could both earth and solar targets with the least possible Drive effort can be achieved.

To the existence of such comprehensive infrastructure certainly stands still a long way to go and so there should be every opportunity to be able to present previously economically usable results become.

For this belongs in particular, the extraction of valuable precious metals and substances from minor planets and their shipment to the earth, as well as energy production in space and their transmission to the earth. The featured here different spacecraft, structures and functional units could for such Purposes cost-effectively Find use.

Ring segment system for large, massive Spacecraft, space stations and space habitats in concrete construction

Not last, possibly to the possibly to mitigate the impression that I have the further development human space flight because of the initially preferred robotic Conquest and exploration of space not so much at heart lie, would like I hereby a possible Method of constructing the casings greater, massive spacecraft, space stations, and space habitats to introduce.

These had the advantage that due to their size and external mass both the Radiation protection (through meter-thick, mass concrete / concrete-like Walls) as well as the protection against the health consequences of long-lasting Weightlessness (by the generation of artificial gravity by Rotation) is.

A the more often Ideas circulated in science fiction publications is the erosion of one Asteroids and its conversion into a spaceship. However, this one has Idea for a longer one ongoing human occupation a fundamental defect. It exists the danger that the asteroid, its components due to its low gravity is loosely held together, breaks apart or internal cavities collapse.

So can even rocky asteroids are so shaken by impacts that the rock (s) with jumps are interspersed.

A more economical one and safer solution might the processing of asteroid rock materials and dusts Breaking, grinding and burning to sand, gravel and cement and for further processing these raw materials for to be the creation of concrete outer shells.

These wrap enable a solid, radiation-proof outer structure in the desired Form and due to their thickness the inclusion of in one of the above Sections described from the outside nachankbaren plug and Screw-on complete drive units. Rock / concrete walls, the provide adequate protection against space radiation, should, according to the prevailing opinion, have a thickness of about 4 m (or thicker).

looks then the diameters of the objects in question, (those of dimensions considered me would be z. B. 108 m diameter for a spaceship and 1000 m ring diameter for a habitat in the manner of a Ringes of the Stanfordian style Torus or later still described mill / lady-stone form) can Doubt arises that it is possible is, these huge masses at all in space.

Is it at all conceivable and possible, Such huge, massive objects at affordable cost to create?

With to be transported from space to space Resources certainly not for the time being. But what about if that Whole is divided into smaller, more affordable portions, free resources available on an asteroid, almost free Transport services by solar glider mate and on asteroids won Fuels, as well as free solar energy for further processing to disposal stand? Should not be used with existing robotic equipment and sufficient time available for such ambitious projects? After all The pyramids are certainly not created in one day Service.

As can now be divided into smaller, easier digestible appetizers of such Mega-Space Construction Projects be achieved?

Mondays and Transportation of space concreting molds

The basic idea is based on the preparation of individual complete rings, z. B. 1 m wide at 4 m thickness, created individually and gradually assembled into a complete spacecraft / Habitat become.

For this will be near the earth Ringantriebsraumfahrzeuge used in the ring body the from skeleton composite skeleton of Betonierformen to Concreting the individual rings of the respective construction project with help clamped by CNT belts or parts. These skeletons would then by winding / applying a z. B. carbon fiber or CNT-reinforced shell Mistake.

The Attachment of the outer skin could supported by space-suitable adhesive method or by welding a basic and Vorbefestigung with eyelets and CNT cords / ropes respectively. To carry out this work would preferably used astronaut-controlled airworthy robots.

These Would work Accordingly, preferably carried out in a near-earth orbit. after the Forms in the ring of the transport vehicle are completely mounted, goes this on the way to the final Installation site preferably in the vicinity a relatively close to the sun, asteroid suitable for material extraction.

The used mold transporter would So with quite low payload on their way to the place of use (only the lightweight designs and possibly the preassembled in the forms Thrustereinheiten would be transported) brought. The direct work of human astronauts would come with First of all, to mount and to set the way for the forms to come to an end.

Everything more would be automatically or remotely controlled by the earth.

The desired End result would be a spacecraft cover, whose concrete segments would be fabricated and assembled in space by robots.

The Thruster units would then by robotic tankers with fuel, the possible also from asteroids, filled from the outside. The empty shell could become then controlled remotely using their own Thruster drive on the way back to the protective Earth magnetic field open, where then the further expansion with Help human astronaut / craftsman could be done.

The first maiden voyage of such a spacecraft with human Crew should then not to Mars, but to an asteroid to lead and the crew should include concrete and steel workers.

Remote control the extraction and processing operations

Also Of course I have asked the question if it at all realistic, by the distance to the asteroids, at the preferred sun-facing location quite once in the course of your orbit in proportion to the earth on the other side of the sun, (ie up to 2 AU away from the earth) at all at remote control too think.

Yet It seems to the current state of human technology this to give no alternative, because human decisions and creativity are necessary, because robotics has not progressed so far to robots to leave such tasks.

As but can be a remote control at the time delay alone by the size Distance arises and also by blocking the radio paths by Objects, such as B. the sun at all to be possible?

The The answer is first by building a high bandwidth satellite communication system supported around the sun through the sensor-assisted Use of semi-automatic sequence programs for the remote-controlled robotic Functional units.

is First, a chain of communications satellites in orbit around the sun, probably the transmission of image and other measurement data even at high required Bandwidth does not pose a problem.

control and mutual communication of the satellites among themselves even the robot should be over a secure internet protocol.

The Stationing of such satellite chains, which are preferably is about smaller thruster ring solar gliders of the kind discussed here, could through very big ones Carrier solar gliders take place, with a magazine dock inner ring, on page 27 of this description was treated, equipped.

So every one would these carrier ships z. B. 12 satellite sailors (this number is simply from the air grasped, but should show the direction of the train of thought) carry with them, the one after the other at the intended location independently of Mothership drop off and their task due to low fuel consumption and the abundant solar energy in principle for a very can perceive for a long time.

The Attachment of the subsidiary units shown in the pre-proposal also on the outer sailor surface sees the inventor / author now as not so cheap, because the controller the mother sailor by the position of the daughter ships in the center of the Mother is easier and less fuel is consumed and because automatic loading and unloading is considerably more difficult here should be.

is after stationing a gapless Satellite chain communication ensured robots could using semi-automatic control mechanisms from Earth by human "robonauts" who are themselves certainly highly qualified scientists (such as astrophysicists) would act, by means of VR techniques (Virtual Reality) are remotely controlled.

Flying material collection container with Bucket holder and closable opening

Around To give an example here, is a raw material extraction robot in the form of a thruster ring vehicle (this time without a sail), at the bottom of a container with a shovel-shaped Receiving opening, the one with a lockable Lid is provided is attached.

This Robot now has the task of asteroid dusts and loose rocks or scree to promote and then return to his mother ship. The processes for the and again mooring has already been described. It would have to be Programs give these operations with sensor assistance.

Of the Robonaut would have to the conveyor robot thus giving the order after knowing the surrounding images and data, in which position he should go to this. The robot would be due its programming with sensor assistance capable of this position at a certain distance (eg 2 m above the asteroid surface, the film and measurement data to send to the earth, as well as taking the desired position to convey and to remain there until the further instructions of the Robonaut arrive.

Of the So Robonaut has the option first to evaluate the data and television pictures at rest, before giving the commands for the next Steps (taking a different position or starting the commodity bucket action) returns.

Of the Robonaut now comes to the conclusion that in this example a removal attempt is worthwhile and gives the instruction to the robot which strength and at what angle, if necessary for how long it will sink into the dust or rubble layer and if he then right back with the help of the pushing up thruster should rise to a waiting position.

This sounds dangerous at, as it is, finally the robot's ion thrusters are not exactly strong and the acceleration from a standing position should therefore not be sufficient to the robot, by the way, for this Task is designed to damage.

A Removal of the dust and possibly also of debris is therefore likely because of the low Gravity and the low surface density / adhesion of the raw material despite the weak forces the ion thruster possible be.

If everything went well, receives the robonaut after the delay break has passed, image and measurement records, the robots are again in a waiting position above the ground, including the level of the raw material container and can the decision for Follow up actions.

A problem is already apparent with this promotion method: It is to be expected that the Bildauf were very poor due to the dust contact. This could be done by using other image capture methods such. As X-ray, radar and the like are mitigated. In addition, the lenses of the optics should have some sort of automatic wipers.

A Possibility, to reduce the accumulation of dust would be like in another Mentioned section, to use only thrusters that accelerate to the surface of the asteroid, So not to the surface out.

Of the conveyor Robot would be there accelerate gently into the ground and then from the distant mothership on a thread with the help of the winds pulled up again from the asteroid.

Also Here again you can see how advantageous the low ejection force of the used ions thruster for can be such difficult tasks.

Also for different equipped robots would be similar customized Sequence programs, however, always similar to the one described here Patterns run, conceivable.

Flying Material collecting container with different gripping arms

One Another application example would be a conveyor robot, the from a clamped in a flying ring material container with Gripping collective arms exists. These arms would be on the container surface or too affixed to the sides and able by their length and appropriate joints both the soil in the vicinity of the container to reach, as well as the collected materials by itself automatically opening To move hatches into the container.

in this connection could Various gripping devices are used such. Eg huge ones Bird-claw-like claws, arm pairs with hands around the an of the human Gripping with both hands to mimic or simply electromagnetic cranes, the magnetic metals or ores.

Here it should be possible be that the robonaut the individual objects that are collected to be, as well as to the gripper indicated that the robot used for salvage. It is not excluded that Programs that perform such activities even fully automatic, developed at short notice can be because it is basically about relatively simple gripping operations.

Definitely there are some other material collection methods for asteroids, which require only relatively simple actions.

The let both procedures and functional units presented here however, the possible uses recognize the use of thruster rings that the on asteroids largely missing back pressure by gravity, usually for the mining of mineral resources is necessary to replace by thruster pressure.

Especially the extraction of rocks and dusts that may be required for concrete processing can be used seems to be possible by simply collecting and scooping be. Whether mine, if justified Assumptions can only show landing on asteroids. Therefor could Among other things, the tools presented here are carried along, which confirm the effectiveness of the collection possibilities indicated.

Space concreting process

The fill Concrete molds with liquid concrete preferably takes place nearby of the asteroid, of which the largest share of raw materials to be won.

Similar to When concreting on earth concrete vehicles are required for this, which mix the constituents of the concrete and on-site in existing Fill in molds. They are in turn filled by special functional vehicles, the Water, sand / dust and cement deliver.

The the conformation holding ring drive spacecraft would during the filling rotate, creating a) Art deco Gravity exactly in the desired Extent generated can be and thus the strength of the exterior of the concrete ring can be influenced.

Around On all sides the temperature required for setting the concrete of positive Celsius degrees could be achieved the shape of one side irradiated by the sun and of the on the other side by means of the airworthy mirrors dealt with in this application heated become.

to Production of liquid concrete could because of the cost-effective Transport also quite on won by different asteroids Material used be, for. B. by bringing of water from an ice-containing asteroid / comet to the nearby Materials of a rocky asteroid obtained from the processing site.

treated have been in this description already methods of collecting and Gaining rocks / boulders and sand / dust material, which is the basis for the recovery of about 70 Percent of concrete material by crushing, grinding, grinding of rocks should be won.

Also the recovery of water, z. B. by evaporation of ice-containing Comet / asteroid material should not be insurmountable technological hurdle with which a further 15% of the raw materials required for concrete production to disposal would.

Out However, it is clear from the above descriptions that not only the concreting molds and the driving ring spacecraft holding and transporting them are required, but a whole fleet of different functional units have to be designed but for the most part used in the here treated drive rings and with these can be transported.

The remaining approximately 15 percent of the required raw materials are occupied by the cement, which is usually obtained from limestone and clays by burning and grinding. However, the Romans used z. As well as volcanic ash, which were mixed with limestone, as a cementitious binder. So there are different possibilities and
Mixtures to make cement.

Also Slags that z. B. as by-products in metal processing accumulate, have cementitious properties.

If and which of the asteroid-based raw materials for cement production are suitable (about the easily recoverable surface dusts?) Should by sampling in sufficient quantity and application tests first on the ground in collaboration with the cement industry.

at the required grinders for material shredding could on the combination of proven mechanical Processes and devices of the concrete industry with the use of the possibly usable in space artificial Rotational gravitation resorted to become. Hereby, the abundance of energy in the near-sun is abundant helpful for operating these devices.

As well In turn, the firing and drying processes are done by laser and mirror functional units with free available standing energy possible be.

Just for the Creation of the required huge mirror units for The use in free space can be lighter, less expensive Constructions are used because the extensive absence of gravity this lightweight design allows more.

As already noted elsewhere, is the solar radiation in the Near the Sun, z. B. at half the distance (0.5 AU) already four sometimes as strong as at ground level.

One Mirror with a quarter the size of a Near-Earth mirror should thus bring the same power at 0.5 AU.

Also Here is again to see what advantages of finding the proximity of the sun for the required production processes because of the lower here necessary Plant size for power generation offers.

Many of these energy-consuming production processes are therefore in the sun, especially due to the abundance of energy in principle cheaper to carry out in space than on Earth, this is especially true if this already a functional also cost-effective transport infrastructure by the use of cargo gliders.

in this connection But it is not just about cost advantages, but about the long-term shift of polluting industries (like the Mining and energy production) into space and thus protection and preserving more valuable, for the food production of important cultivated land on earth, as well as the Securing the not too far away on earth flagging Supply of raw materials for certain substances.

preferred Design of a concrete ring spacecraft

13 Figure 4 shows the design of a preferred end-product of space-ring-segment concrete construction, namely a round spacecraft of the shape of a dowel stone, on the narrow sides of which, as on the other spacecraft and structures treated here, are also fixed outwardly projecting complete guard units , These should, however, be refilled from the outside with fuel, as a complete replacement for refueling should not be useful.

In 13.a is the cutaway profile of several nested rings of the spacecraft body and in 13.b is the profile of the lenses, which are themselves put together again of several rings to see.

There it should be a spacecraft that does not land itself, but only for provided for transport in open, radiation-prone space is needed it's not an aerodynamic shape. Therefore, more emphasis was placed on functionality, simple Design and in particular laid on an outer shape, the possible easily assembled with simply shaped components can, what leads to this form but getting used to.

At the narrow spaceship side are the individual in the drawing Ring layers can be seen, which make up the flat, cylinder-like hollow body, which is bounded by two end caps at the ends.

Of the valuable interior in the center of the disc would be on both sides (above and below) for Landing and docking facilities are kept free, which are easy for free spaces can act, which are provided with ferromagnetic metal plates on which the docking vehicle with the help of (electric) magnet attached.

It would be, however including the use of the magazine docking devices covered in this application for many Spacecraft (eg multiple communication reconnaissance and functional units) conceivable and meaningful.

Prefers would be here an execution with free landing area and entrance lock for astronauts on a disk and a docking magazine for several supplementary units on the opposite disc of the spaceship.

Around the central docking rooms would be around Solar cells for the power supply and antennas / dishes for transmitting and receiving equipment, or measuring devices as well as cameras arranged.

Of the Diameter of this spacecraft, that by means of the Seitenstrahlthruster turns around its center and thus especially at the inner radius the lateral outer walls artificial Earth gravity creates, should be in this example 100 m. With its 4 m thick walls it would have an enormous mass. As a thruster are likely because of the big to moving mass rather chemical, but refueling drives come into question.

To take Suppose the spacecraft is near the L1 librational region together and the outside ones Complete thrust units from the outside with gained in space Fuel filled Service.

The on the way to bring this massive spacecraft is likely the absolute weightlessness prevailing there in both directions, so relatively easy both towards the sun and towards the earth be, because the normally heavy body would weigh initially hardly anything and just so to speak "downhill" in the direction of then more and more will be set in motion gravitational.

his later Use is likely such a construction probably as a so-called cycler Find. In doing so, the spacecraft becomes highly elliptical Orbit whose peaks are aimed at the targets to be achieved, z. B. an earth orbit with a peak within the earth's magnetic field and the second peak near Mars.

advantage This use as a cycler is that the spacecraft is in one Orbit, with no or little further correction of the Orbit needs. It always revolves in its orbit further. The fuel consumption is therefore very low.

These Use form is therefore especially for very massive and therefore difficult and fuel-intensive to navigate spacecraft almost on.

Indeed must be in In such a case, always the time to "get in" by the potential passengers waiting become.

Mass of the Concrete Wall spacecraft

It is assumed by a spacecraft whose interior is 12 m in the height and 100 m in diameter and that's the shape of a mill or Damesteines has.

Of the Outer diameter of the vehicle is about 4 meters thick Walls thus 108 m, the height 20 m. For assembly, 12 concrete rings averaging 1 m Width (even if the dimensions by the profile are different) and 4 m thickness as well as 2 end plates of 4 m wide and a diameter of 108 m needed.

The density of the concrete is assumed to be 2.4 to / m ³ .

A fully developed and loaded concrete spaceship according to this design should therefore have a mass of less than 220,000 tonnes at more than 94,000 m ³ internal volume.

This appears in comparison to a pressure-stabilized glass-steel construction, From the enormous mass certainly as a disadvantage.

Why So this design?

The high mass of the spacecraft proposed here has undisputed Disadvantages, in particular with regard to the required acceleration forces in later operation, however, the advantages weigh the disadvantages of the current state of the art Technology by far

The The main advantages are that the technology for obtaining the Raw materials as well as the construction of the shell is simple and considers the inventor's for humanity as fast as possible solution the problem of radiation exposure through the meter-thick concrete wall promises.

As soon as Humanity is capable of metals, glass and CNT materials in space with reasonable effort to win, process and certainly, at least the endplates will do more as 80 percent of the body's mass through a CNT steel and replaced glass construction.

For the first Radiation-safe manned spacecraft with gravity should however the "windowless" version is sufficient.

Moreover, one should not be deterred by the aforementioned high mass values. Such a thing has brought mankind in the form of the pyramids by far more primitive means, employing thousands of slaves and the need to fight against earth gravity.

But what are those hundreds of thousands of tons of earth weight, though these in the near-weightlessness of asteroids an amazing low actual Have weight and can still be moved by robots?

Of the In any case, inventors assume that the required raw materials in bulk by simple open pit mining with the methods described here can be won.

at the metal extraction for a relatively thin one Spaceship hull Although the masses of the metals used in the end are in total considerably smaller, but to obtain sheets, huge quantities of ore have to be processed be and additional Melting and rolling processes take place before a much more labor-intensive design process can be started.

At the Concreting, however, only the required raw materials are mixed, promoted into forms and brought to setting.

Assembly of the Concrete ring segments

To the bonding is every single ring still in its shape, which is already suspended in a fully mobile spacecraft. Grundsäztlich there is therefore the possibility merging the nestable rings with their pendants by these spacecraft carry out allow.

Besides that is but it is also possible additionally or instead of the drives of the transport vehicle possibly still to be added or already introduced in the forms from the outset own thruster of the ring units to use.

To the joining of two rings, these are tightened on the sides by means of tensioning devices, consisting of CNT straps / ropes and corresponding end hooks clamped together at the outer edges. This is preferably done with a total of two tensioner pairs diagonally outside the ring diameter opposed, where the distances each 90 degrees.

These Tensioner units remain even after completion of the mold as reinforcement at the spaceship.

The rings are after 13.a shaped so that after joining at the outer interfaces results in a wedge-shaped, outwardly tapering recess with blunt wedge end. This recess is covered with a wider CNT masking tape (by sticking or wrapping around the entire body and clamping).

thereupon the resulting wedge-shaped cavity is filled with concrete and this brought to setting.

Of the last ring on both sides is the outermost ring of the end plates.

In These are the ever smaller inner rings of the end plate stuck, which are also profiled so that they are intertwined Own. These rings are also secured with tensioners, with masking tape covered and the remaining recesses filled with concrete.

To the binding of the last recess, the hull is completed. As far as the thruster units were already inserted into the molds before, can these are now filled with tankers from the outside with fuel.

Besides that is also the attachment of screw-on thruster units to the desired Make possible.

All the thruster units would be provided with transmitters and receivers that would monitor the filling state, the working pressures and temperatures, as well as a remote control allow.

There every single unit can be controlled, the empty envelope is from this Time maneuverable and able to make her way back in a closer Earth orbit where they are used by human astronauts Can be taken and further expanded.

Concrete ring Space Habitat

The o. a. mill stone-like Shape of the spacecraft is certainly also suitable for a space habitat; however, the habitat should be much larger, at least about 1000 m in diameter, because from this diameter generation of artificial Gravity of a G no inconvenience / dizziness at are to be expected of the human inhabitants.

at smaller diameters would be However, this is the case because the rotational speed corresponding elevated would have to be.

advantage this millstone form across from a habitat in torus form is the much larger, more usable volume.

Compared to the The first windowless spacecraft should be the habitat at least Own glass outer walls. this could done so that three of these mill stones under reduction the inner partitions be placed on a total of 4 m thickness and the two outer respectively an end plate made of glass or concrete / glass CNT glass composites receive.

It would thus a core unit surrounded by concrete, which is completely through protected this and "windowless" would be increase the inner and outer strength, could these and also the ring outdoor area Additionally coated with CNT fibers.

The both outboard Units could for agriculture and leisure time as greenhouses / parkland be used, with damage / destruction of the Cover plate on the other side still has a backup would.

The Illumination of the side facing away from the sun would be done by mirrors.

One Another feature of a preferred habitat design would be a cylindrical concrete inner ring in the center the disk plane completely pass through the habitat and is provided at the ends with lock gates. With this serves inner tube as radiation-protected An entry lock and entrance lock for spacecraft and astronauts.

torus

Also the realization of the torus form is with the help of the concrete ring segment system possible.

For this the individual rings are shaped in the same way as in the Mill Stone shape however, with the difference that you are inward accordingly the desired Rejuvenate ring size, so that when joining together all wide sides and all the rejuvenating sides a torus arises.

The Cover plates are no longer needed in this case.

Explanations to the drawings and list of reference numerals

The following list of reference numbers is based on the list of the pre-proposal submitted on 26.07.2002 and adds these to the numbers 5 (Inner ring), 6 (Outer ring of a daughter structure, which is inserted into the inner ring of the parent structure) and 7 (Plug and screwdriver units, which applies to both applications.

The numbering of the drawings of the previous application (last drawing was 7 ). The first drawing of this supplementary application therefore begins with 8th ,

Thrusternummerierungen refer to the individual thrusters in the respective drawing.

The Drawings are far from true to scale as the Size of too can move descriptive objects in the square kilometer range, while the structural parts of the structures such. B. the pipe diameter the pipe segments of the outer ring are more in the centimeter range can.

The Reference numerals are divided into the areas

1

Drive units, outer ring and central drive units / modules

2

Solar sails / tethers

3

Payload platform

4

Launcher shipping bracket for ring segments

5

inner ring as a docking station and / or device holder

6

outer ring a daughter structure

7

plug and screwthruster units

To 8th

8th illustrates a coupling unit, which serves both for docking smaller spacecraft / functional units in parent structures, as well as various devices for dealing with and / or to clamp objects by means of winches, which may be equipped with different gripping-holding device.

By the replacement of the inner functional unit may be a spaceship Space structure easy for converted another purpose become.

These used in several of the developments presented here In the opinion of the inventor also represents the most important improvement / supplement to the inventions presented in the pre-proposal, since the docking and loading / unloading in Center of the disc a significant improvement in the possible uses offers these ring structures, in particular for modularization and the robotic flow control.

To 8.a

8.a shows a dual docking station that allows docking above and below the disk plane of a thruster-ring spacecraft or corresponding spacecraft structure. That is, two daughter units could simultaneously put on or take off.

The double docking station will just like the docking inner ring after 8th in the center of the outer ring with the help of straps, but possibly also with the help of ropes or heavy-duty CNT threads o. Ä. Clamped.

For additional protection against vibration / vibration is also an attachment of the two end rings 5.4 using ropes or CNT threads 5.3.1 , possible, similar to tent poles from top to bottom leading to the outer ring tensioned and fastened there (see also this 8.b ).

It is a lightweight scaffold consisting of 3 tube rings or also ring discs, which run through vertical tubes 5.3 kept at a distance and stabilized.

Basically here the same accessories (Winches, docking brackets, etc.) come for use, as already in the notes to the single docking station in detail discussed.

To 8.b

8.b shows a magazine docking station, which allows to transport spacecraft and flying functional units in larger quantities with a mothership in this particularly favorable center of the disc, as well as automatically dock and put down.

A preferred application would be z. B. the transport of whole swarms of news and Beob Attention satellites to their place of deployment. To z. For example, there is constant communication around the sun and in order to maintain planets or moons or to observe the sun.

Although in the present drawing, only a dock with 6 berths is located, in principle, however, in particular because of the flat design of the thruster ring space vehicles still significantly more units by extending the vertical tubes 5.3 and additional docking brackets are docked.

For balance reasons, there are in each case an equal number of docking points above and below the inner ring 5 , In the middle there would have been room for another docking station in the present example, but this became a payload platform 3 used.

In the drawing is a small drive-ring spacecraft in the lowest magazine dock above the payload platform 3 , When docking in the dock need the docking brackets 5.1 the top berths are driven outwards. This is done with the help of an electric worm motor 5.5 who the rack-toothing 5.4.1 drives at the bottom of the brackets.

The Attachment in the dock is magnetic and / or electromagnetic by using corresponding ferromagnetic materials in Connection with permanent and / or electromagnets.

At the here provided greater height of the vertical tubes 5.3 It is advisable to use these from both sides at the ends by tightening of safety cords 5.3.1 to fix. An additional increase in stability would be through the use of tailpipes or rings 5.4 (S. 8.a ) possible.

If it is at the mothership about a large glider (with z. B. 1000 m diameter, also appears a dock, the two Pages 10 to 20 m above the plane of the disc protrudes, and z. B. a diameter of 20 meters, not disproportionate to the overall size of the vehicle.

With relatively little material, can Here, therefore, by eliminating external walls large volume capacity achieved be the stability the structure and maneuverability hardly affect because of the central storage.

The mentioned glider would have a dock with 20 m diameter and a height of 10 m on both sides of the disc out (ie total height of the storage room 20 m) about 6,300 m ³ storage area and there is still a lavish space for the placement of solar cells and the solar sail.

you Imagine what uncertainties you have because of flying around / beating Cargo with square mastsseglern in this order of magnitude after earlier Solar sailors designs would be exposed.

at such sailors would be Furthermore to the targeted here automatic docking certainly not to think.

His full efficiency However, this transport system can be suitable only in symbiosis with this Achieve functional units that are themselves airworthy.

The ideal complement to this cargo ship would be a system of standardized, self-transporting containers. This could be realized in the form of round containers, which in a thruster ring as the payload platform 3 be clamped in the present drawing.

The Ion thrusters are well suited to several hundred kilograms heavy spacecraft over longer Moving distances is demonstrated by SMART I, ESA's European space probe Time in an impressive way. However, the containers would only have shorter distances z. B. travel from an asteroid to the glider.

To avoid misunderstanding, the inventor sees very well that these possibilities are limited to the weightless or almost weightless space and other drive solutions have to be found for dealing with the gravitation of larger moons or even planets. In interplanetary space, however, most of the itineraries will take place under weightless conditions and for that The thruster-ring spacecraft in conjunction with the solar sail drive are ideally suited and therefore offer the opportunity to build a cost-effective space infrastructure.

9 is intended to represent despite the elliptical shape of the drawing round spacecraft, which performs the function of a giant carcass. It is intended to collect and dispose of space junk, and to catch and transmit material thrown by Mass-Drivers could, however, also be used to increase the orbit of satellites that are running out of fuel.

The size Strength This vehicle results from the weakness of its ion drives. It can approach carefully to the objects to be captured and This avoids billiards and consumes relatively little Treibsoff. The range of the vehicle could still by using solar sails in the thruster ring as additional fuel-free drive can be improved.

The trapped objects are only affected by the slightly higher speed that the Flugkäscher needed and the constant Acceleration in the cheesecutter held.

Complementary but also the attachment of gripping arms and the like possible on the ring.

The Unopened opening of the cheesecutter makes it possible nevertheless, the objects by counter acceleration again in the desired direction to dismiss.

To build:
The outer thruster ring is here with considerably more Thrustern ( 1.6 ) equipped to propel the vehicle with the disc surface ahead as with the thrusters 1.5 which are responsible for the rotation about the pole of the disc and for the movement with an edge of the spacecraft ahead.

This is also understandable because the butcher should also be with the open area be operated ahead.

The butcher 2.7 is in the inner ring 5 hooked, in turn, in the outer ring 1 is clamped by straps. The straps also carry the solar cells necessary for the energy supply in the form of the solar cell ring 2.5 , The outer ring 1 could connect directly to the solar cell ring, if the only drive to be the ion drive.

Should however, the spacecraft in addition with a solar sail for extension the service life and range are provided even more room for the solar sail, which in this case only from the outer ring to the solar cell ring would be enough required.

In the drawing are also still the main cameras 1.2.1 of which two are opposite each other on the other side. These cameras are close to the cameras 1.2.2 on the ion-thruster units 1.5 are attached.

Of the Inventor puts so much emphasis on the placement of cameras, because this for a robotic vehicle remotely controlled by humans are important.

With regard to the arrangement presented here, the cameras have to replace the two human eyes for remote control. It is therefore important if these are both for the direction of travel with the area forward (cameras 1.2.1 ) as well as with the leading edge in the same place, so that no disorientation occurs.

Switching the orientation of the cameras 1.2.1 on the cameras 1.2.2 Therefore, when the arrangement is made as proposed, the lifting of the head to look up can be compared. Since both pairs of cameras are available in duplicate, it is also possible to switch with a rotation of the plane of 90 degrees.

As an inner ring is present, of course, the already presented gripping and holding devices after 8th be used.

To 9.a

The spacecraft in 9.a is different from the vehicle in 9 only in that a bag is hung in place of the cremator in the inner ring.

thought is this type of application for the extraction of larger quantities of raw materials on and in the vicinity of asteroids. A bag is still the lightest transport container and can be easily closed by lacing after use and then be replaced by another.

The close and open the sack could by appropriate devices on the inner ring with the help of side winches automatically performed become.

To 10

10 shows that it is quite conceivable to give a thruster-ring spacecraft a high initial acceleration by combining it with a chemical rocket (eg the booster of a launcher).

The rocket is here by means of tethers 2.1 and the straps 5.3.1 both with the inner ring 5 as well as with the outer ring 1 lashed.

To the burnout of the rocket could the thruster-ring spacecraft unlock the connection and the flight with your own Continue drive.

To 11

11 shows a not yet completed solar power plant (solar power station - SPS) without drives and solar cells based on a flying ring 1 with an inner docking ring 5 and a string with straps 2.1 ,

Right below is the one connected to the solar power plant via a power cable Energy transmitter too see.

The attachment of the solar cells should by clamping the straps between the holding plates 2.1.1 , which are screwed into prepared screw holes on the back of the solar cell housing done. The attachment of the straps is shown on the bottom left.

To 12

12 shows a Schraubthruster unit, which is intended to be screwed into the ground of an asteroid by means of the large rotary lever and the depressed thrusters of a flying ring.

For this purpose, the expiring in a tip screw and tank body of the thruster unit has a screw thread 7.1.3. In addition, a filler neck is available for refueling.

purpose screwing it is the asteroid by favorable placement of several to maneuver remote-controlled thruster units.

To 12.a

This is a Doppelthruster unit for screwing on thick, solid surfaces, z. Concrete. The thruster unit sits on the screw-on plate 7.2.7 on through the screwed into the ground.

To 12.b

shows a double thruster unit for insertion, along with the receptacle 7.2.4 , This is intended to be embedded in the subsoil prior to use of the Thruster unit (eg concreting with the concreting forms discussed in this application.

1

drive ring

1.1

Propulsion segment

1.1.1

central drive unit

1.1.2

central drive module

1.2

Empty segment

1.2.1

Main stereo camera

1.2.2

Thruster Tower Camera

1.3

Side beam segment

1.4

Gurthalterung

1.5

double thruster pages

1.6

double thruster up down

1.7

Mounting opening

1.8

Mounting Splint

1.9

Lance holder

1.9.1

locknuts

1.9.2

Counter-half pipe

1.9.3

Splintstangen

1.9.4

Holding rank-half pipe

1.9.5

tank pipe

1.9.6

Electro-stranded

1.10

lance

1.10.1

ionizer

1.10.2

accelerator

1.10.3

neutralizer

2

Solar Sail

2.1

Retaining straps

2.1.1

Gurthalteplatten

2.1.1.1

Gurthalte screws

2.1.1.2

Gurthalte locknuts

2.2

Edge-belt

2.3

Ladegurt

2.4

Sail film / fabric

2.5

Solar cell ring

2.6

Solar cell Anay

2.7

Käscher network

2.8

Flight Ring transport bag

3

Payload platform

4

Launcher shipping bracket for ring segments

4.1

transport head

4.2

Transport head-end support

Under group 5 all the devices for coupling are listed, even if they are on the outer ring 6 the daughter unit

5

Inner ring of the mothership / ring structure - s. For this 8th

5.1

Docking bracket

5.1.1

supporting fork

5.1.1.1

Fork rod connecting part

5.1.1.2

Fork-stop

5.1.2

Lower mounting clamp

5.1.3

Upper mounting clamp

5.1.4

Fastening screw

5.1.5

Fork retaining plate

5.1.6

Fixing nut and bolt

5.1.7

electric lock

5.1.8

Fork ends-threaded

5.1.9

Electric lock retaining plate ( 2.1.1 )

5.2

winches

5.2.1

rope o. Strap o. Thread or hawser

5.2.2

Winds ring

5.2.3

Winds snap hook

5.2.4

Glory flying ring

5.2.4.1

5.2.4.2

5.2.5

Docking magnet permanent

5.2.5.1

switchable elec. Docking magnet

5.3

Docking vertical tube

5.3.1

tether

5.4

Graduation Ring

5.5

Docking bracket

5.6

elec. Screw motor

5.7

ferromagn. Graduation washer

5.8

power cable

6

Outer ring / drive ring the docking daughter structure

7

screw or Steckthruster unit

7.1

Schraubthruster unit

7.1.1

lance

7.1.2

Tank- and screw body

7.1.3

screw thread

7.2

Plug thruster unit

7.2.4

receptacle

7.2.5

Sleeve stop plate

7.2.6

Thrusterstopplatte

7.2.7

Aufschraubplatte

contents leaf Docking station or charging station (FIG. 8) 1 Electromagnetic coupling and decoupling by means of an annular disc made of ferromagnetic material as docking inner ring 4 Mechanical dock mount (Figure 8) 4 Mounting a mechanical docking bracket (Fig. 8) 5 Mother-daughter grandson units as transporter, power supply and landing units (Lander / Prospector) 5 Coupling inner rings in large space structures 6 Docking process (here on rotating space structures) 7 "Flying space-waschers" as space debris and rubble collector, to increase satellite orbits with trawl or bag as well as a capture unit for mass-driver transport (Fig 9 and Fig. 9.a) 9 Carrier with inner ring as a repair and maintenance unit and towing equipment 11 Use of the inner ring for space tractors (space tug) and cargo transport 12 Inner ring winches with different functions (Fig. 8) 12 Replacement of holding and carrying straps 2.1, 2.2 and 2.3 by highly tear-resistant "threads" in the form of a covering 15 Ferromagnetic fastening clips as fastening holders on retaining straps 17 (Private) economic application possibilities 18 Finding, extracting and processing raw materials in space 19 Is the inventor's claimed landing ability or hoverability above an asteroid, including arrival and return with low-accelerating thrusters, realistic at all? 20 What mass would have z. B. a 100-m mother sailor with 5-m lander? 21 Landing on, or hovering over an asteroid 22

Collect / Win of asteroid material 24 use of the inner ring in cargo ships as a cargo and cargo handling unit 25 booster as capable of coupling Function unit for accelerating a spacecraft with inner ring 26 double Inner ring as a double docking device 26 Magazine Dock inner ring for coupling several daughter-ring spacecraft 27 mobile Solar Cell Space Power Plant (Solar Power Station - SPS) 27 Solar power plants Additionally the energy supply of the earth 30 Solar power plants for melting and heating 30 Thrusterring spacecraft as a mirror or lens 31 Thrusterring spacecraft as mobile receiving and transmitting units 32 screw and pluggable complete thruster units 32 screw in of screw objects on small planets 33 method and tools for extracting resources on minor planets Utilizing the rotary lever and thruster pressure of a thruster-ring spacecraft 34 pluggable Thrustereinheiten 34 use of the rotary lever for Drill brackets and other screwing devices 35 outlook 35 Ring Segment System for large, massive Spacecraft, space stations and space habitats in concrete construction 38 is it at all conceivable and possible, Such huge, massive objects at affordable cost to create? 39 Assembly and transportation of space concreting molds 40 Remote control the extraction and processing operations 40 Flying remote-controlled collection container with bucket holder and lockable opening 42

Flying Material collecting container with different gripping arms 43 Space concreting process 44 preferred Design of a concrete ring spacecraft 46 Dimensions of concrete wall spacecraft 47 Assembly the concrete ring segments 48 Concrete ring Space Habitat 49 torus 50 Explanations to the drawings and to the list of reference numerals 51 reference numeral 57 Summary 59 designation of the inventor and declaration of intent according to § 23 Patent law 60 claims 61 This contents 65

drawings

( 1 - 7 were submitted with the pre-proposal of 24.07.2002)

8th Inner ring as docking and charging station

8.a double inner ring as dual docking and charging station

8.b Magazine docking station (here for 6 Thrusterring mini-spaceships

9 Flying Ring Spacecraft as a Space Scavenger

9.a Flying ring as a sack spacecraft
(for the volume transport of raw materials, such as ores, ice, etc.)

10 Flying ring with additional chemical booster

11 Solar power station (Solar Power Station - SPS) with transmission unit

12 Screw-thruster unit

12a Screw-thruster unit

12b Plug-thruster unit

Claims (13)

Docking and charging station for spacecraft or space structures with outer ring 1 ( 1 ) according to one or more of claims 1-17 of the prior application, characterized in that a) this in its center with a docking device in the form of a rigid inner ring 5 (S. 8th ), which is used for coupling and depositing daughter ships or functional units and additionally allows the handling and attachment of objects / cargo, b) the inner ring by straps or ropes or (thread) clothing in the outer ring 1 c) the inner ring can be composed of pluggable pipe segments, d) the conversion of a equipped with an inner ring spacecraft or a space structure can be done by simply replacing the entrained in the inner ring functional unit, e) in the inner ring entrained functional unit itself also with an airworthy drive outer ring 1 to 1 can be equipped, which facilitates a robotic conversion. Inner ring according to claim 1 as a docking station and coupling device for functional units, characterized in that a) he provided with docking brackets is where these can be carried out as follows: b) as electromagnetic Mounts, by attaching electromagnets on the inner ring and (ferro) magnetic contacts on the docking object, c) as electromagnetic holder, by attaching electromagnets at the docking object and (feno) magnetic contacts and electromagnets on the inner ring, d) by additional Equipped with power supply lines and contacts for power supply the daughter unit through the mother unit, wherein power line and Contacts through execution the holders can be made by means of electrically conductive materials, e) as a mechanical docking bracket f) as a mechanical docking bracket with additional electromagnetic fastening. Mechanical dock mount 5.1 for docking spacecraft or functional units consisting of a support fork 5.1.1 , a stop 5.1.1.1 , Clamps 5.1.2 and 5.1.3 , Fork bracket 5.1.5 , Fixing nut 5.1.6 and electric lock 5.1.7 , characterized in that a) the docking object of at least three on the inner ring 5 attached mounting forks 5.1.1 holding the holding device of the docking object (eg, specially provided handles or in the form of an outer ring 6 ) from three sides, b) the holding device of the docking object from the fourth side through the electric lock 5.1.7 is secured, wherein the locking bolt of the electric lock attached to the docking object with locked holding device under the lock bolt lock 5.1.1.1 leads through, c) the retaining fork 5.1.1 consists of two parallel bars whose ends are formed on one side for receiving the holding devices of the docking objects and by the Schließriegelsperre 5.1.1.1 are connected, wherein the straight rod ends of the other sides are provided at the head sides with internal threads, d) the attachment of the retaining fork 5.1.1 by complete insertion through holes provided for this purpose both through the tube of the inner ring and by one of the retaining clips, wherein the protruding from the tube of the inner ring straight ends of the retaining fork by means of screws, from the outside by the fork bracket 5.1.5 into the internal threads of the retaining fork, be screwed, the rods of the retaining fork as Durchsteckbegrenzung thickening (stop node 5.1.1.2 ). Inner ring according to claim 1 as a loading and clamping device, characterized in that a) this with electric winches 5.2 is provided with straps, ropes or threads 5.2.1 5) straps, ropes or threads 5.2.1 both without further device for load attachment serve (eg by knotting the cargo) as well as at the free ends with gripping, holding or other devices can be equipped b) as gripping or holding devices, in particular electromagnets, rings 5.2.2 , Snap hook 5.2.3 , Robot hands or claws, excavator buckets can be used, c) whereby the use of functional units that are mounted on (miniature) Flugringen, as other wind equipment is possible. Double docking device ( 8.a ) for thruster ring spacecraft and functional units according to one or more of claims 1 to 17 of the prior application, characterized in that a) it allows the simultaneous docking or storage of two drive ring spacecraft on both sides in the center of a drive ring mothership, b) they from a middle ring 5 and two conclusion rings 5.4 which are connected by several (preferably 4) vertical tubes, c) by means of straps or ropes or threads 2.1 is clamped in the center of the drive ring 1. Magazine docking device ( 8.b ), for thruster ring spacecraft and functional units according to one or more of claims 1 to 17 of the prior application, characterized in that a) it allows the docking of several stacked spacecraft in the center of a drive ring mothership, b) they simultaneous docking or Depositing two drive-ring spacecraft on both sides in the center of the mothership allowed, c) with the help of straps or sides or threads 2.1 in the center of the drive ring 1 is clamped, d) from a middle ring 5 exists where several pipes are mounted vertically, Thrusterring spacecraft as a space killer after one or more claims 1-17 of the petition, thereby marked that a) it equipped with an inner ring according to claims 1-4 is in which a butcher hooked is, with the objects captured in space, or collected can be. Thrusterring spacecraft as a material collector after one or several claims 1-17 of the Pre-proposals, characterized in that a) it with an inner ring according to claims 1-4 equipped where is a sack-like container is mounted, with which objects in space can be collected. Solar power space power plant according to one or more of claims 1-17 of the pre-application, characterized in that a) it is equipped with an inner ring according to claims 1-4, b) it is provided with an airworthy transmitting unit for electricity, which serves to transfer energy to the destination and in the inner ring 5 of the space power plant can be carried, c) it with a covering of preferred straps 2.1 is provided on which the solar cell modules are attached, e) wherein the attachment with retaining plates 2.1.1 can be done, which are screwed from below over the straps to the housing of the solar cells. Transport system consisting of load solar gliders after one or more claims 1-17 of the petition, characterized in that a) he with a dock device is equipped according to one or more of claims 1-6 and b) airworthy Load container with a thruster ring according to claims 1-17 available are able to independently dock and undock in this docking station. Spacecraft according to claims 1 to 3 of the pre-proposal and 1 to 6 of that application, characterized that the cross section of the tubes of the docking station inner ring and / or the outer ring is rectangular, square or polygon shaped. Spacecraft according to claims 1 to 3 of the petition and 1-6 This application is characterized in that the shape of the docking station and / or the outer ring rectangular, square or polygon shaped. Spacecraft according to claims 1 to 3 of the petition and 1-6 This application, characterized in that the shape of the docking station round or oval or triangular.