DE102004004543B4 - Spacecraft docking and docking station, space solar power plant, space miner - Google Patents

Abstract

Thruster solar sailor according to the patent no. DE 102 34 902 B4 .
characterized in that
the thruster solar sailor has a loading and docking system consisting of a loading and docking station for coupling and dropping at least one docking capable daughter unit, wherein the charging and docking station
a) alternatively
• from a rigid inner ring (5), or
• an inner ring (5) which, when aligned horizontally, is connected to a double docking and charging device by means of several vertical docking tubes (5.3) with parallel or superposed end rings (5.4), or
• an inner ring (5) which is connected to a plurality of docking vertical tubes (5.3) which, when viewed parallel to one another from the horizontally oriented inner ring (5), continue upwards and downwards and form a magazine dock,
wherein the ring body or bodies consists of at least one iron-containing annular disc for magnetic coupling or of at least one annular tube, and wherein
b) the loading and docking station by straps ...

Description

The application relates to a thruster solar sailor and a ring segment assembly system after the main patent DE 102 34 902 B4 ,

outgoing from the task of the main patent is intended both the thruster solar sailor as well as the ring segment assembly system with a loading and docking station be extended.

These Task is with the thruster solar sailor according to the features of the claim 1 and with the ring-segment mounting system according to the features of the claim 2 solved.

The additional application also relates to reference numerals and drawings of the main patent ( 1 - 7 ).

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 Connection with attached to this winches he allows safe handling of cargo and other objects through the clamping possibility safely accelerated and maneuvered in the ring without knocking around can.

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.

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

One relatively large Solar sail mothership, for example, 100 m in diameter could the docking station a sail-less subsidiary vehicle with a diameter from Z. B. introduce 10 m close to an asteroid. The thruster and fuel quantity this daughter ship would be here on the short-term purpose of the landing and extraction optimized from raw materials to 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 providing a mothership, the and transport to the site 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 through the introduction corresponding coupling classes and mutual provision compatible infrastructure.

The introduction and separation more airworthy, but not or only partially Long-distance airworthy Spacecraft as a subsidiary ship and long-range motherships would have too another advantage; the near-earth motion of space projects could under control less, the security of the earth committed to a special extent Organizations remain access to space without smaller units to block.

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 the activated thruster of a starting subsidiary unit whose Overcome holding power 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 means Inner ring will be explained.

This would have advantages as additional Securing the coupled objects, for example in the event of a power failure to the electromagnets or simply as a power-saving measure, or as reinforcement the coupling in spacecraft required for reentry into planetary atmospheres are meant.

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 is shown on an inner ring, which by means of several (in Example 4) docking mounts ( 5.1 ), in which the outer ring of a daughter unit is docked, has been 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 ) by both the tubular body and by one of the clamps ( 5.1.2 ) or ( 5.1.3 ), which already have prepared wells at the designated locations.

The plug-in process is interrupted 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 ) are pressed around the tubular body of the inner ring.

The externally threaded ends of the retaining fork ( 5.1.1 ) are 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 by the fork plate ( 5.1.5 ) are 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 can preferably by screwing an electric lock retaining plate ( 5.1.9 ) on the underside of the lock, whereby the belt is clamped between the underside of the lock and the retaining plate.

Mother-daughter grandchildren units as transporters, Power Supply and Landing Units (Lander / Prospector)

One Another application example of the interleaving 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 transmission 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 tensile strength with simultaneous conductivity and insensitivity across from Space influences.

advantage this solution is that batteries are saved and on the energy reception and Transmission facilities can be dispensed with entirely, with no additional Conversion losses arise.

The idea of sending a power generation unit in space through a cable or by sending the power to a power consumer is certainly not new, e.g. B. was you in U.S. Patent 6,194,790 B1 applied, in this case to 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 makes possible 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 inner rings in large 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 scrap 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 of 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) the rotation of particularly massive large objects and subsequent starts is extremely energy consuming.

The However, it may be necessary to shut down the rotating object be avoided by using the inner ring as a docking station, when the docking spacecraft also rotates itself. This will not only saved energy, but also z. B. at 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 also allow rather deliberate maneuvers due to their very low thrust, the ship approaches the station gently rotating and sets shortly before reaching the docking mounts with the counter thrust of the thrusting downwards and thus accelerating 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 brackets ( 5.1 ).

The fine alignment of the coupling vehicle could, for. B. by 4 in each case 90 degrees apart from each other on the outer ring ( 6 Positional position transmitter mounted on the spacecraft, which are each at 4 also at 90 degrees on the inner ring ( 5 ) of the object to be approached mounted opposite to each other almost vertically 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 located in the basic position and the approach can start.

• 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 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. As solar power space power stations or space stations, as well as often used trajectories especially in front of flying debris, space junk and the like be slotted.

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 To accomplish such tasks would be a flying ring spacecraft that out hardly exists any more, than from a drive ring and into this one hinged 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 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 becomes a web of carbon nanotube fibers (CNT) proposed, 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 could funded Ores, or metal-bearing rocks from the place of origin to the destination or to a distribution node without having spacecraft would be required.

A another possibility would be that Mass-Driver Slings of magnetic material containers around z. For example, to transport dust and sand-like 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 shows a flying butcher (mainly intended for collecting space debris and increasing satellite orbit), 9a shows a flying sack, which is rather intended for use as an airworthy raw material collection container.

shipborne with inner ring as repair and maintenance unit as well as towing device

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 to exchange after the pre-application and since this at the same time with a Tank are provided, thereby simultaneously "refuel".

Also refueling with an outside lying tank port provided larger thruster units could through Such maintenance robots are made with thruster ring.

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 and then again with the second smaller Thrustersegler coupled and separately the way back can compete.

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

By the inner ring, which is very large Units quite considerable dimensions can take (about a 1000 m spaceship with 100 m or 200 m Inner ring) it is possible Objects, e.g. Satellites or small asteroids in the center of the spaceship and accelerate in a different direction without the objects held in the ring all at once a life of their own develop.

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 ) with 4 different functionalities.

The Recording of four differently equipped winches took place only to illustrate the different uses.

meaningful it goes without saying at least two, ideally 4 identical winches for secure attachment inside the structure available to have. By appropriate tightening of the winds, so for each one a uniform tension arises, can the loads to be transported safely and without changing the course or accelerations uncontrollably to beat around, clamped become.

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 top 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 pole solar gliders for cargo transport, which were used in the previous solar sailer designs.

Of the Inventor / author can not imagine how the recording, or the discharge of cargo in such a huge pylon sailor should be done without the spacecraft by jumping cargo endangered is, in particular by risk of breakage of the mast bearing or risk of damage of the 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 attach to the satellite to be towed, this with the help of the ion drive to the intended orbit and continue until the end of the period of use at this remain attached 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 holders (in particular electromagnets) or gripping devices which are fastened to the ends of the cables / straps of the cable 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 you can then dismiss it again or even first through the winch flying units transported to their destination (if it is in 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 used already today (eg. B. by the French Company Nanoledge) are manufactured industrially.

This Material is incredibly tear-resistant, Space suitable and also still electrically conductive.

So could 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 there is no gravity to overcome in space, such a "string" of objects could pull or 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 could 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 fabric

Not only (but also) the o. a. enormous resistance of the Nanotube material, but also the expected low mechanical loads, have brought the developer to his original concept of belt fittings reconsider 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 an environment in the tons heavy masses no, or hardly have a weight or are in free fall condition and the regular load 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?

To 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 give off a relatively rigid surface on which payload can be attached almost anywhere on the plane (eg, by simply tying and knotting, but also using appropriate fittings, such. 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 to 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 curious.

By the separate knot of each thread would be even in the destruction of individual Threads through Meteorite impact continues to have a certain strength of structure given, as long as not the outer ring as well damaged becomes.

Also in the stringing technique could on experiences in the covering of badminton rackets by Use similar 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 to thread through, 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 a mounting bracket on straps

Even though for "normal" spacecraft in the case of payload attachment, the above holding net or stringing method because of the lower mass in most cases certainly the better Be solution likely, also has the belt fastening method z. For example, it continues to be legitimate for giant objects.

width Strips of ferromagnetic material could be exactly to the desired Positions attached to the fastening and holding straps of the holding net become and would make it possible Magnetically attach objects 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 possibilities

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. You 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.

The less fuel has to be transported, the more power remains for the payload or the lower the turnaround for the spacecraft, which can be designed accordingly weaker (and thus more cost-effective).

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

Finding, winning 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 Thruster ring solar glider with the help of the normally for the control used thruster possible is over to take samples from them and even if necessary to land and then ascend again or this by the entrained lander carry out allow.

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 is 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. After the return transport by the mother sailor in the earth orbit he could then a second time Uncouple from the mothership and with the help of the parachute on the Land the earth.

Should he survive this undamaged, would a reuse after replacement of the thruster nothing to stand in the way.

is the landing ability claimed by the inventor, or hoverability over one 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) creates it, the orbit of 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 (1200 g thruster weight and about 100 g of surrounding tube) would weigh 31.2 kg.

In contrast to the 80 kg fuel required for Smart I, each 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 be on the trial an 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.

The outer ring is internally covered with 0.5 mm CNT threads, which are set at a distance of 25 cm and hold the inner ring in the center of the spacecraft. Mother sailor (with 6 cm outer ring, inner ring, holding net thread distance 25 cm) CNT outer ring d = 100 m about 60,000 cm ³ = 78.0 kg (1.3 g / cm ³ ) CNT inner ring d = 5.5 m about 3,260 cm ³ = 4.2 kg CNT solar sail d = 100 m about 7826 m ² = 55.0 kg (7 g / m ² estimated) CNT holding net of about 800 threads about 47100 cm ³ = 61.0 kg (1.3 g / cm ³ ) with a total length of approx. 60,000 m 12 double thruster units with fuel = 40.0 kg all in all = 238.2 kg Lander (without solar sail with 6 cm outer ring, holding net thread distance 10 cm) CNT outer ring d = 5 m about 2,960 cm ³ = 4.0 kg CNT holding net of about 100 threads about 275 cm ³ = 0.4 kg with a total length of approx. 350 m 6 double thruster units with fuel = 12.0 kg all in all = 16.4 kg

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 according to "high" gravity obviously, it does not seem to be that hard on one Land asteroids.

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?

To take As an example, let's take a look at the Lander discussed above Payload including the an asteroid derived materials 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 the 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, however, regard the sampling as extremely challenging because of the extremely low gravity. They want to fire a projectile with a small pyrotechnic charge into the asteroid surface, with which a part of the surface is to be destroyed in order to subsequently 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 expelling 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) adapted Miniature drives of this kind produce, which then again a Start from the gravitational 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.

The disadvantage, however, is then the lower efficiency and the danger caused by the exiting burning gases endanger the mothership when coupling. However, since the thruster ring vehicles can accommodate quite a few thruster species on the ring, in addition to the ion drive of the one Set of cold gas thrusters for asteroid starts possible.

Collect / recover 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 robot arms, or excavator-like gripping devices pointed.

So z. B. a solar glider or spacecraft with thruster ring hover over an asteroid and there by means of winch flying rings ( 5.2.4 ) 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 This procedure is that on dusty surfaces 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, the Thruster Ring spacecraft discussed here are 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 hereby presented thruster ring spacecraft or parent-subsidiary combinations therefore, in my opinion in connection with a solar sail 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 an / an airworthy 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 could z. B. replenishment to a space station or a minor planet by means delivered to a payload platform, which then stays there, while the returning one Solar sailors in exchange a second, already with the won there Docking resources loaded platform, which then at the destination (z. B. a near-earth space station) in turn against another already loaded replenishment payload platform.

Booster as a coupling functional unit for acceleration 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 available.

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. Because of 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 double Docking loading facility

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

8b shows an inner ring docking and charging unit, which makes it possible to accommodate a larger number of thruster ring spacecraft and to connect and disconnect.

• 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 unterschiedlich 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 differently equipped subsidiary units, eg. B. to reduce asteroid raw materials with different equipment.
• c) Transport of several container units by a container cargo ship.
• d) Transport of several inner ring flight and power units, by a workshop mothership specialized in mounting these units on non-moving satellites Supply electricity.

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.

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

The Arresting of the daughter ships in the scaffolding takes place in this case into the scaffolding protruding rack mountings by means of electric motors and screw thread into and out of the docking room can be.

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

Mobile Solar Cell Space Power Plant (Solar Power Station - SPS) With U.S. Patent 6,194,790 B1 From 27.02.2001, a space-based solar power plant / solar power generation station based on a solar sail, whose sail fabric is provided with a photovoltaic power generating photovoltaic coating, was 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 through the Thruster rings and possibly the Sails 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 ion drive with ejection speeds from 60 km / sec. was operated, which is a doubling of the previous possible ejection speeds means. The locomotion of 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 11 shown.

The orientation of the power plant to the sun is similar to the orientation of a solar sail. By rotating the power plant, the drift generated by the sun's radiation can be compensated be alternately rotated so that it approaches the sun and then rotated again so that it can be removed and thus held a middle position.

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. Transmitters and consumers are not affected by the power cables in theirs Mobility restricted.

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 with only 0.05% (page 66, Plate 4.1).

Yet they prefer for the power supply of the actual space elevator, so to speak the Elevator car (climber), which rises by engine power at the lift "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 front of 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.

11 shows such a power plant. Basically, it is a thruster ring spacecraft with plenty of solar cell arrays and / or a power sail that with an inner ring after 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 z. B. instead of the laser unit, a subsidiary ship, which acts in principle as a flying outlet, are used when nearby places need to be powered. It is intended to be used over an asteroid, in which the power supply unit only a few hundred meters above the Kleinplaneten surface floats and supplies the power via a cable to the "socket unit" at the site on or above the asteroid surface.

Solar power plants to supplement the Energy supply of the earth

Also the transfer of energy through microwave radiation has despite the high conversion losses by conversion their meaning, namely to electricity from solar power plants (SPS) to send to earth. The transmitted energy does not have to be produced by burning fossil matter on earth and this carries thus contributing 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. One must not overlook that such a space-based large power plant connected to a Laser a very powerful 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 in particular, 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. 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.

There also the transport of these raw materials to the earth when using Solar sailors cost-effective that could be Extraction and simultaneous basic processing (melting) of such Substances may also be economical if this work is done by robotic Function units takes place.

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

In the above-described methods for the extraction / processing of raw materials by Melting / heating with laser use, the energy loss through conversion is relatively high.

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

A not quite as exact, but not always in such a significant Extent required bundling is however also when using a equipped with mirrors or lenses Thrusterring spacecraft possible whereby 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 Focus lying objects / materials.

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 become mobile space transmitters and receivers.

Remote control of the extraction of raw materials 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 near location certainly once in the course of your orbit 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 Answer is: first by building a high bandwidth satellite communication system around the sun, supported supported by the sensor 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 sailors done with a magazine dock inner ring included in 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 daughter units shown in the pre-proposal also on the outer sail area sees the inventor / author now as not so cheap, because the control of the parent sailors by the location of the daughter ships in the center of the mother is easier and less fuel is consumed and because the automatic loading and unloading should be considerably more difficult here.

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

Explanations to the drawings and list of reference numerals

The the following list of reference numbers is based on the list of the 26.07.2002 submitted to and supplemented by paragraphs 5 (Inner ring) and 6 (outer ring a daughter structure used in the inner ring of the parent structure becomes). It is therefore valid for 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 sail / tethers
• 3 = Payload platform
• 4 = Launcher transport holder for ring segments
• 5 = Inner ring as docking station and / or device holder
• 6 = Outer ring of a daughter structure

To 8th

8th represents a coupling unit, which serves both for docking of smaller spacecraft / functional units in mother structures, as well as various devices for dealing with, or for clamping objects by means of winches that can be equipped with different gripping and holding devices.

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

8a 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 sealing rings ( 5.4 ) by means of ropes or CNT threads ( 5.3.1 ), possible, similar to tent poles from above be stretched leading to the outer ring and fixed there (see also this 8.b ).

It is a lightweight scaffold consisting of 3 tube rings or also ring discs, which are supported by vertical tubes ( 5.3 ) are 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 observation satellites to their location. To z. B. a permanent Communicate around the sun and maintain planets or moons to be able to or for sun observation.

In the present drawing, although only a dock with 6 berths is shown, 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 mounts 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 available for 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, the docking brackets ( 5.1 ) of the top berths are driven outwards. This is done by means of an electric screw motor ( 5.5 ), the rack toothing ( 5.4.1 ) on the underside 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 remove these from both sides at the ends by tensioning 5.3.1 ) to fix. An additional increase in stability would be achieved by using the 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 volume 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 at square mast sailors on this scale after earlier Solar sailer designs would be exposed.

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

However, this transport system can only be fully used in symbiosis with it reach suitable functional units, which are also 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.

Around no misunderstanding arise to let the inventor look very well, that these possibilities restrict to the weightless or almost weightless room and for the Dealing with the gravitation of larger moons or even planet other drive solutions need to be found.

in the interplanetary space, however, is the major part of the travel routes under weightless Conditions take place and for that The thruster ring spacecraft are in conjunction with the solar sail propulsion ideally suited and therefore offer the possibility of a low-cost space Build infrastructure.

9 in spite of the elliptical shape of the drawing, it is intended to represent a round spacecraft that 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 Gently approach the objects to be captured and thus billiards avoid and consume 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. additional However, it is 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 double thruster units ( 1.6 ), which are to propel the vehicle ahead with the disc surface as with the double thruster units ( 1.5 ), which are responsible for the rotation about the pole of the disc and for moving 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 ), which in turn in the outer ring ( 1 ) is clamped by straps. The straps also carry the solar cells required 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.

The drawing also shows the main cameras ( 1.2.1 ), two of which 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 used both for the direction of travel with the surface 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, it can be compared with raising the head to look up. 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 using the 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 tension straps ( 5.3.1 ) with both 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 fabric with straps ( 2.1 ).

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

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.

Left below the attachment of the straps is shown.

1

drive ring

1.1

Propulsion segment

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 array

2.7

Käscher network

2.8

Flight Ring transport bag

3

Payload platform

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-holder 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

elec. Screw motor

5.6

Docking bracket

5.6.1

Ironing toothing

5.7

ferromagn. Graduation washer

5.8

power cable

6

Outer ring / drive ring the docking daughter structure

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 bulk 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

Claims (12)

Thruster solar sailor according to the patent no. DE 102 34 902 B4 , characterized in that the thruster solar sailor has a loading and docking system consisting of a loading and docking station for coupling and depositing at least one docking capable daughter unit, wherein the loading and docking station a) alternatively • from a rigid inner ring ( 5 ), or • from an inner ring ( 5 ), which when horizontally aligned by several docking vertical tubes ( 5.3 ) with termination rings lying parallel above or below ( 5.4 ) is connected to a double docking and charging device, or • from an inner ring ( 5 ), which is equipped with several docking vertical tubes ( 5.3 ), which are parallel to each other from the horizontal inner ring ( 5 ) seen from up and down and form a magazine dock consists, wherein the ring or body of at least one iron-containing annular disc for magnetic coupling or at least one annular tube, and wherein b) the loading and docking station by means of straps ( 2.1 ), Ropes or thread coverings in the outer ring ( 1 ) of the thruster solar glider, and wherein c) the loading and docking station is provided with a plurality of docking and / or charging devices with which daughter units held in the docking station and / or cargo / objects by means of winches ( 5.2 ) are held and handled, with the respective winds ( 5.2 ) with a rope, strap, thread or hawser ( 5.2.1 ) is fitted, are attached to the free end gripping or holding devices. Ring segment mounting system according to the patent no. DE 102 34 902 B4 , characterized in that the ring-segment mounting system includes a ducking system consisting of a loading and docking station for coupling and depositing at least one docking daughter unit, wherein the loading and docking station a) alternatively • from a rigid inner ring ( 5 ), or • from an inner ring ( 5 ), which when horizontally aligned by several docking vertical tubes ( 5.3 ) with termination rings lying parallel above or below ( 5.4 ) is connected to a double docking and charging device, or • from an inner ring ( 5 ), which is equipped with several docking vertical tubes ( 5.3 ), which are parallel to each other from the horizontal inner ring ( 5 ) seen from up and down and form a magazine dock consists, wherein the ring or body of at least one iron-containing annular disc for magnetic coupling or at least one annular tube, and wherein b) the loading and docking station by means of straps ( 2.1 ), Ropes or thread coverings in the outer ring ( 1 ) is clamped in the thruster-ring spacecraft or space structure mounted from the ring-segment mounting system, and wherein c) the loading and docking station is provided with a plurality of docking and / or loading devices holding subsidiary units in the docking station and / or Cargo / objects with the help of winches ( 5.2 ) are held and handled, with the respective winds ( 5.2 ) with a rope, strap, thread or hawser ( 5.2.1 ) equipped at the free end gripping or holding devices are mounted. Thruster solar glider according to claim 1, characterized in that the loading device at least one winch ( 5.2 ), each with one on the winch rope, belt, thread or on the winch hawser ( 5.2.1 ) attached winch flying unit, in particular in the form of a winch flying ring ( 5.2.4 ), which itself is capable of flight and therefore selectively control the load or respective object and can attach to the load connected to the winch flying units, preferably magnetic or electromagnetic, holding or gripping devices, wherein by tightening several winds ( 5.2 ) is pulled to the desired charging voltage, the load or object to be loaded in the charging station and held there. Thruster solar glider according to claim 3, characterized in that the winch flying units in the form of flying rings ( 5.2.4 ), which are used for collecting rock, ore, dust and sand-like asteroid raw materials and that the flying rings ( 5.2.4 ) are equipped with gripping and collecting devices for the asteroid raw materials, which are intended by means of the winches ( 5.2 ) from the loading and docking station to the asteroid surface for material intake. Thruster solar sailor according to one of claims 1-4, characterized in that in the loading and docking at least one daughter unit with a rigid outer ring ( 6 ) by means of mechanical docking supports ( 5.1 ), wherein the at least one subsidiary unit is Thruster solar gliders or thruster-ring spacecraft, and wherein the docking mounts ( 5.1 ) one on the inner ring ( 5 ) by holding attached retaining fork ( 5.1.1 ), the outer ring ( 6 ) comprising at least one subsidiary unit from three sides, and connecting this connection by means of an electric bar attached to the daughter unit ( 5.1.7 ) is backed up from the fourth page. Thruster solar glider according to one of claims 1-4, characterized in that in the loading and docking at least one daughter unit with a rigid outer ring ( 6 ), wherein the at least one subsidiary unit is a Thruster solar glider or a thruster-ring spacecraft, and that the inner ring ( 5 ) or the closing rings ( 5.4 ) of the docking station is a ferromagnetic annular disc, on which the outer ring ( 6 ) couples the at least one daughter unit by means of magnets and / or electromagnets, or from which he decoupled again with appropriate polar alignment by repelling. Thruster solar glider according to one of claims 1-6, characterized in that the loading and docking station as a magazine loading and docking station for at least one subsidiary unit with a rigid outer ring ( 6 ), wherein the at least one subsidiary unit is a Thruster solar glider or thruster-ring spacecraft, and this is equipped with movable docking mounts attached to the docking vertical tubes ( 5.3 ) and from the docking brackets ( 5.6 ), which are equipped with a bracket toothing ( 5.6.1 ) and by means of electric screw motors ( 5.5 ) into and out of the docking station. Thruster solar glider according to one of claims 1-7, characterized in that the loading and docking station is equipped with at least one daughter unit, which via a thruster outer ring ( 6 ) equipped with double thruster units ( 1.5 . 1.6 ) and at the same time serves as a holder to which the holding devices ( 5.1 . 5.6 ) of the docking station keep them inside. Thruster solar glider according to one of claims 1-8, characterized in that the charging device ( 5 ) in its interior with a chipper ( 2.7 ), with which objects in space are captured or collected. Thruster solar glider according to one of claims 1-8, characterized in that the charging device ( 5 ) in its interior with a closable bag-like container ( 2.8 ) is provided as a material collector, are collected with the objects in space. Thruster solar glider according to one of claims 1-8, characterized in that it is extended to a mobile solar power station by a) he with a docking and charging station ( 5 ), to which an airworthy subsidiary unit, which may be a power supply unit or a laser or microwave transmission unit, is provided by means of a live pulling cable ( 5.8 ) via a winch unit attached to the station ( 5.2 ), and b) the outer ring ( 1 ) of the Solar Power Station with a net-like covering made of straps ( 2.1 ), preferably made of straps or CNT threads, is attached to the solar cells for power generation, the attachment with holding plates ( 2.1.1 ), which are screwed over the fabric to the solar cell housing, so that the fabric is clamped between the housing and holding plates. Ring segment mounting system according to claim 2, characterized in that for mounting a mobile or stationary solar power station a) this with a docking and charging station ( 5 ), to which an airworthy subsidiary unit, which may be a power supply unit or a laser or microwave transmission unit, is provided by means of a live pulling cable ( 5.8 ) via a winch unit attached to the station ( 5.2 ), and b) the outer ring ( 1 ) of the solar power station with a net-like covering made of straps ( 2.1 ), preferably made of straps or CNT threads, is attached to the solar cells for power generation, the attachment with holding plates ( 2.1.1 ), which are screwed over the fabric to the solar cell housing, so that the fabric is clamped between the housing and holding plates.