RU2088491C1 - Long-endurance manned orbital cable complex - Google Patents

Abstract

FIELD: space engineering. SUBSTANCE: complex has two module orbital stations with base modules and space vehicles to be docked which are connected by means of several cables and towed space vehicle connected with one of orbital stations by means of captive cable; one cable is load-bearing and other cables are adjusting. Each orbital station contains assembly module mated to base module; first assembly module is provided with main winch mechanism for extending and retracting the main cable which is wound on drum of main winch mechanism; other end of main cable is secured on second assembly module which is provided with adjustable winch mechanism for extending and retracting ropes; at one end, adjusting ropes are wound on drums of adjustable winch mechanism and at other end, they are secured on first assembly module. Complex includes also long electric cables; assembly modules include truss structures provided with cable winch mechanisms for extending and retracting the long cables wound on drums. Truss structures are provided with electric plasmas contactors electrically connected with ends of cables and coupling units. Long cables are used for conducting electric current for electrodynamic maintenance, raising and correction of complex orbit, electrodynamic generation of electric energy, radiation of radio waves and other operations which require long current conductors. EFFECT: enhanced reliability. 3 cl, 1 dwg

Description

 The invention relates to space technology, mainly to long-term manned orbital stations.

 Known manned orbital stations, consisting of two parts connected by long flexible elements, using rotation around their center of mass to create artificial gravity in the inhabited compartments due to the action of centrifugal forces.

 In the project K.E. 1895 Tsiolkovsky (KE Tsiolkovsky Dreams about earth and sky. M. From the Academy of Sciences of the USSR, 1959, pp. 59-62) describes an empty metal ball with a crew inside, connected by long strong chains with a rather significant mass, not exceeding much the mass of the ball itself, and this whole system moves in orbit around the asteroid and rotates around its center of mass. With a ball speed of 50 m / s and a chain length of 500 m, i.e. when the angular velocity of the system's own rotation is about 0.2 rad / s in the ball due to centrifugal forces, a gravity equal to that of the earth develops. By changing the rotation speed, the speed of artificial gravity can be reduced or increased. K.E. Tsiolkovsky described the imaginary subjective sensations of a person and some physical phenomena in conditions of such artificial gravity.

 In the project, Yu.V. Kondratyuk 1929 (Lyapunov E.V. Station outside the Earth, M. Voenizdat, 1963, p. 140) describes an inhabited base moving in orbit around the moon, consisting of four living quarters located on the tops of the tetrahedron and interconnected by aluminum trusses. In order to create artificial gravity, this base is connected by a cable several tens of meters long with a counterweight and this system is brought into a state of rotation around its center of mass.

 The G. Obert project of 1923 (Lyapunov B.V. Station outside the Earth, M. Voenizdat, 1963, pp. 114-118) describes the Earth satellite station, consisting of two cabins connected by a wire rope and rotating one relative to the other.

 Similar projects of a later period are known.

 The creation of artificial gravity by rotation with an angular velocity of the order of 0.1 1.0 rad / s around the common center of mass of two parts of the orbital station, connected by a cable tens or hundreds of meters long, is associated with side effects, including a biomedical one, caused by the action of Coriolis forces.

 In addition, the continuous rotation of the orbital station complicates or makes it impossible to perform many technical operations and scientific research (the orientation of the station relative to the Sun, maintaining and correcting the orbit, docking and undocking of spacecraft, observing the Earth’s surface, etc.). Periodic stops of rotation of the station to perform such actions and resume its rotation would require large amounts of fuel or electricity, as well as create significant inconvenience to the crew.

 Space stations are known containing blocks spaced from the main part of the station on long flexible elements.

 The project (Erica K. The Future of the Space Industry. M. Engineering, 1979) describes a space settlement containing living quarters, agricultural and industrial sections, with a nuclear power plant located on a long cable.

 In the project of G. Noordung (Lyapunov B.V. Station outside the Earth, M. Voenizdat, 1963, p. 118-121; Bubnov I.N. Kamanin L.N. Inhabited space stations - M. Voenizdat, 1964, p. 165 166) a station is described that consists of three parts: a toroidal rotating living room, a cable connected to it by a solar power plant and an observatory connected to it by a flexible pipe.

 Known manned orbital stations containing an astrobuxer, which is withdrawn from the main part of the station on a cable or flexible conduit, are designed to capture and pull the docked spacecraft to the station (Bubnov I.N. Kamanin L.N. Inhabited space stations M. Voenizdat, 1964, p. 39; Belyakov I.T. Borisov Yu.D. Fundamentals of space technology M. Mashinostroenie, 1980, p. 105 106).

 Each of the well-known orbital stations, consisting of several parts connected by long flexible elements, allows us to implement, as a rule, only one direction of practical application of orbital cable systems and the design features of the above-mentioned orbital stations do not allow us to simultaneously realize a large number of those possibilities that could be implemented using orbital cable systems.

 In addition, in the above-considered orbital stations, the neighboring parts of the station are interconnected, as a rule, with only one cable or cable. In this case, the cable combines the functions of both the load-carrying and conductive element. This significantly complicates the repair and replacement of these cables, cables and related devices, and also makes it almost impossible to restore the station's operability in the event of a cable or cable breakage, for example, when it is interrupted by a meteoroid, in the event of a cable short circuit, etc.

 In the above-considered orbital stations, it was also assumed that the devices for accumulating and releasing cables and cables were either absent or could be placed inside the inhabited compartments of the station or on its external elements. This can complicate the operations associated with the need to change the lengths of cables and cables, reduce the safety of the crew of the station or require the crew to perform complex installation and repair work in outer space.

 The closest analogue of the present invention is a long-term manned orbital cable system comprising two modular orbital stations with base units and docked spacecraft connected by several cables and a towed spacecraft connected by a tethered cable to one of the orbital stations (Bekey I. Tethers open new space space options // Astron. Aeron. -1983, V. 21, No. 4, -PP. 32-40). This cable system consists of two modular platforms composed of empty fuel tanks and interconnected by several cables of 10 20 km length. The upper platform is designed for astrophysical research, and the lower platform for Earth observations, as well as for the mooring of orbital ships. A spacecraft is assigned from the upper platform on the cable, designed to launch payloads into higher orbits.

 The known cable complex has, although to a lesser extent than others, limited functional and operational capabilities.

The technical result of the present invention is the ability to perform the following operations and scientific research in flight in low Earth orbit:
lengthy research and experiments simultaneously at several altitudes with a difference of tens and hundreds of kilometers, as well as in the upper atmosphere,
research, observations and experiments in space using significantly spaced measuring and active devices with an interferometric base of tens and hundreds of kilometers,
observations of the Earth’s surface and atmosphere using photo and radar equipment towed on a cable at low altitudes,
crew work, research and experiments under artificial gravity with levels up to tenths of earthly gravity,
simultaneous independent or joint work of two crews at different heights with the provision of information and energy communications between them,
descent from orbit and return to Earth of modules, ships, satellites, payloads and waste after their separation of the complex without fuel costs or with reduced fuel costs,
transfer to other orbits of modules, ships, satellites, payloads and waste after they are separated from the complex without fuel costs or with reduced fuel costs,
launching of spacecraft into orbit, their approach and docking with the complex with reduced fuel costs,
return from other orbits to a complex of modules, ships, satellites, payloads, waste without fuel costs or with reduced fuel costs,
electrodynamic maintenance, increase or correction of the complex’s orbit without fuel consumption due to the interaction of electric current in cables with the Earth’s magnetic field,
electrodynamic generation of electricity on board the complex due to the interaction of cables with the Earth’s magnetic field,
other studies, experiments and technical operations requiring the use of long cables and cables in space.

 The specified technical result is achieved by the fact that in the known cable system one of the cables is made of the main power and the others are adjustable, each orbital station contains an assembly and assembly module docked to the base unit, the first assembly and assembly module is equipped with a main winch mechanism for releasing and tightening the main power cable, which is wound from one end onto the drum of the main winch mechanism, and from the other end is fixed to the second assembly-mounting module, the second assembly-mon azhny winch unit provided with an adjustment mechanism for ejecting and retracting the adjusting rope, and control wires with one ends are wound on winch drums adjusting mechanism, and the other ends fixed on the first aggregate-mounting module.

 In addition, mainly the complex contains lengthy electric cables, and the assembly and installation modules contain enzyme structures on which the docking assemblies, electric plasma contactors and cable winch mechanisms are made for releasing and retracting lengthy cables wound on drums, the ends of each cable being wound on cable drums winch mechanisms made on the enzyme structures of the opposite assembly modules and are electrically connected to the contactors.

 In a preferred embodiment, at least one orbital station comprises a mooring module docked to the base unit and a docking docking module connected to the mooring module by a tethered cable, a mooring winch mechanism for releasing and retracting the tethered cable wound from one end onto the drum the other end of the tethered cable is fixed to the tethered docking module, a towed spacecraft is docked to the tethered docking module, outside the berth modulus mechanism configured fumbling spacecraft harness connection module on the base unit and back.

 The drawing shows a General view of the complex.

 The long-term manned orbital cable system consists of two modular orbital stations of the lower station 1 and upper station 2, connected by the main power cable 3, adjusting cables 4 and cables 5. Orbital stations 1 and 2 consist of base units 6 and 7, respectively, and docked to them interchangeable spacecraft 8 and 9, assembly and mounting modules 10 and 11, berthing modules 12 and 13. Berthing modules 12 and 13 are connected by tethered cables 14 and 15 to tethered docking modules 16 and 17, to which the tugs are docked spacecraft 18 and 19. Inside the assembly and assembly modules 10 and 11 there is a main winch mechanism 20 and an adjusting winch mechanism 21 for releasing and retracting the main cable 3 and adjusting cables 4 wound on drums. Inside the berthing modules 12 and 13 there are mooring winch mechanisms 22 and 23 for the release and retraction of tethered cables 14 and 15 wound on drums. The assembly units 10 and 11 contain truss structures 24 and 25, on which there are cable winch mechanisms 26 and 27 for releasing and retracting cables 5 wound on drums, electric contactors 28 and 29 and docking units 30 and 31. On berthing modules 12 and 13 there are re-linking mechanisms 32 and 33.

 The work of a long-term manned orbital cable system is as follows.

The complex is deployed in near-Earth near-circular orbit by performing the following operations:
Launching and docking with each other of the base units 6 and 7, interchangeable spacecraft 8 and 9, modular assembly modules 10 and 11, berthing modules 12 and 13, towed spacecraft 18 and 19.

 Delivery to a complex of crews, equipment, cargo, fuel, etc.

 Assembly of truss structures 24 and 25, installation of cable winch mechanisms 26 and 27, electric plasma contactors 28 and 29, docking assemblies 30 and 31, and other assembly and assembly work performed by the crew during spacewalks.

 the breeding of the orbital stations 1 and 2 by controlled release of the main cable 3, adjusting cables 4 and cables 5, respectively, by the main winch mechanism 20, the adjusting winch mechanism 21 and cable winch mechanisms 26 and 27.

 The sequence of performing the above operations to deploy the complex in orbit may be different. For example, interchangeable spacecraft 8 and 9, berthing modules 12 and 13, and docking docking modules 16 and 17 can dock to base units 6 and 7 both before and after the separation of orbital stations 1 and 2, both before and after mounting trusses designs 25 and 24.

 The deployed complex moves in a near-Earth circumcircular orbit in a stable vertical position, supported naturally by the action of the gravitational-centrifugal gradient. In this position, the orbital stations 1 and 2 are located one above the other, and the main cable 3 connecting them, the control cables 4 and cables 5 are tensioned.

 The lengths of the main cable 3, the adjusting cables 4 and the cables 5 and the forces of their tension are changed by releasing and pulling them, respectively, with the main winch mechanism 20, the adjusting winch mechanism 21 and cable winch mechanisms 26 and 27. The main cable 3 is usually in a fixed state and carries the main the load, its release and retraction is carried out only when the orbital stations 1 and 2 are breeding or approaching. The control cables 4, when they are regulated to release and retract, carry out partial or lnuyu unloading the main rope 3, the stabilization of its tightening force, damping of longitudinal and transverse vibrations complexes. In case of damage, destruction or replacement of the main cable 3, the adjusting cables 4 carry a full load until the main cable 3 is restored or replaced. Cables 5 do not carry loads, only their slight tension is maintained, which ensures that there is no sagging and galling of transverse vibrations. The tie ropes 14 and 15 are usually completely drawn into the berthing modules 12 and 13 and are released and retracted by the mooring winch mechanisms 22 and 23 to retract and bring the tethered docking modules 16 and 17 when performing dockings, orbital maneuvers, studies of the upper atmosphere and other operations.

Within the framework of the deployed complex, research and experiments are being carried out simultaneously at both orbital stations 1 and 2, as well as simultaneously at orbital stations 1 and 2 and towed spacecraft 18 and 19 with tethered cables 14 and 15 released. Moreover, using instruments and sensors placed on Orbital stations 1 and 2 and towed spacecraft 18 and 19, are performed:
subtle radio studies of the Sun and planets, research of space and terrestrial radio emissions, measurements of the orbits of space objects using large interferometric bases, studies of the ionosphere, gravitational and magnetic fields of the Earth, meteor showers with a synchronous height section,
active study of near-Earth space, in particular, the dynamics of the ionospheric plasma, for example, by creating an ion cloud on a towed spacecraft 18 with simultaneous measurements on a towed spacecraft 19.

 other studies and experiments requiring a significant separation of devices and sensors in height.

The towed spacecraft 18 with scientific equipment is lowered on a tethered cable 14 to very low altitudes, up to the upper atmosphere. In this case, the following are performed:
upper atmosphere studies using a long-running towed research probe,
experiments on hypersonic flow around towed aerodynamic models,
low-altitude photography and radar studies of the atmosphere and the Earth's surface by towed equipment,
other studies and experiments at low altitudes and in the upper atmosphere using towed equipment.

 The crews of the lower orbital station 1 and the upper orbital station 2 live and perform basic work in the base units 6 and 7, sometimes passing through the docking nodes into interchangeable spacecraft 8 and 9 for research and maintenance operations. Crews also go out into outer space for assembly, assembly and research operations. Information communication between the crews of orbital stations 1 and 2 is carried out via a radio link or cables 5. Cable 5 also transfers electricity between orbital stations 1 and 2.

 Under the influence of gravitational-centrifugal forces at orbital stations 1 and 2, artificial gravity arises, which reaches values of 0.015 g at a distance between orbital stations 1 and 2 of 100 km and 0.15 g at a distance of 1000 km. The crews of orbital stations 1 and 2 constantly live and work in conditions of this artificial gravity, which improves their comfort. When the tethered cable 14 or 15 is released, respectively, on the tethered docking module 16 or 17 and the towed spacecraft 18 or 119, more intense artificial gravity occurs than at orbital stations 11 and 2. With a distance between the orbital stations 11 and 2 of 1000 km and the length of the tethered cable 14 or 15 1000 km artificial gravity on a towed spacecraft 18 or 119 reaches half the earth's gravity. Under conditions of such artificial severity, medical, biological, material science and other experiments are performed that require the absence of weightlessness. In addition, the movement of fuel and other liquids between containers is carried out by their natural overflow under the influence of artificial gravity.

 In the orbital flight of the deployed complex, the lower orbital station 1 has a drawback, and the upper orbital station 2 has an excess of orbital speed compared to what a free spacecraft would have in a circular orbit of the same height. Therefore, any object (module, ship, container, etc.) separated from the lower orbital station 1 or from the upper orbital station 2 will go into an elliptical orbit, respectively, with a reduced height at the perigee or with an increased height at the apogee. The magnitude of the corresponding change in the height of the orbit will be about three distances between the orbital stations 1 and 2, i.e. tens and hundreds of kilometers. By using this effect, transfer to other (higher and lower) orbits is carried out, as well as launching of modules, ships, satellites, payloads, waste, etc. to the ground. by their simple separation (undocking, dropping) from the lower orbital station 1 or from the upper orbital station 2 without fuel costs or with reduced fuel costs.

 To transfer an object, for example, a removable spacecraft 8 or an object docked to the docking unit 30, into a lower orbit or to launch it to Earth, this object is separated from the lower orbital station 1 and, due to the lack of orbital speed, switches to a new orbit, whose height at the apogee is equal to the orbit height of the lower orbital station 1, and the height at the perigee is three distances between the orbital stations 1 and 2. For a long time this object moves in a new orbit or due to aerodynamic the can enters the dense layers of the atmosphere and cease to exist, or down to earth in a given area. To transfer to a higher orbit, the object is separated from the upper orbital station 2 and, due to the excess of orbital speed, switches to a new orbit whose height at the perigee is equal to the height of the orbit of the upper orbital station 2 and the height at the apogee is three times higher than between orbital stations 1 and 2 If necessary, additional correction of the new orbit of this object is carried out, while the fuel consumption will be significantly less than with conventional interorbital maneuvers.

 For objects separated from the tethered docking modules 16 and 17 when the tethered cables 14 and 15 are released, the corresponding change in the orbit will be even greater than when the objects are separated from the orbital stations 1 and 2. This value is approximately six distances from the tethered docking module 16 or 17 to the center of mass of the complex, i.e. can reach thousands of kilometers. Due to this effect, the transfer to significantly higher or lower orbits, as well as the rapid descent to Earth of modules, ships, satellites, payloads, waste, etc. by diverting together with the tethered docking module 16 on the tethered cable 14 from the lower orbital station 1 or together with the tethered docking module 17 on the tethered cable 15 from the upper orbital station 2 with the subsequent separation (undocking) of these objects from the tethered docking module 16 or 17.

 To transfer a significantly lower orbit to an object, for example, a towed spacecraft 18, as well as to quickly descend to Earth, this object, connected (docked) with a tethered docking module 16, is diverted with it on a tethered cable 14, manufactured by the berth by winch mechanism 22, it is undocked from the tethered docking module 16 due to the lack of orbital speed, it switches to a new orbit whose height at the apogee is equal to the height of the orbit of the allotted tethered docking module 16, and the height in perigee below it at six distances to the center of mass of the complex. Since the height of the new orbit at the perigee affects, as a rule, less than the radius of the Earth, this object very quickly, during a half-period of revolution, falls to the Earth. To transfer to a much higher orbit an object, for example, a towed spacecraft 19, this object, connected (docked) with a tethered docking module 17, is diverted with it on a tethered cable 15, issued by the quay winch mechanism 23, is separated from the tethered of the docking module 17 and due to the excess of the orbital speed, transfers to a new orbit, the height of which at the perigee is equal to the height of the orbit of the assigned tethered docking module 17, and the height at the apogee is six times lower than the price tra mass of the complex. After detaching the object from the tethered docking module 16 or 117, this module is again pulled to the orbital station 1 or 2 by pulling the tethered cable 14 with the mooring winch mechanism 22 or 23. Similar operations can be carried out with interchangeable spacecraft 8 or 9, which are previously using the mechanism reloading 32 or 33, respectively, reloading from the base unit 6 or 7 to the tethered docking module 16 or 17 as a towed spacecraft 18 or 19. If necessary, Additional correction is Busy new orbit of this object, the fuel consumption will be considerably lower than in conventional interorbital maneuvers.

 When docking various objects (modules, ships, etc.) with the lower orbital station 1 or upper orbital station 2, to ensure zero oncoming speed, it is necessary that the spacecraft to be docked move in orbit that does not coincide with the orbit of orbital station 1 or 2. Since the lower orbital station 1 has a lack of orbital speed, an object docked to it, for example, a removable cosmetic device 8 or an object docked to the docking unit 30, must move in orbit with a reduced peri EEM. Since the upper orbital station 2 has an excess of orbital speed, an object docked to it, for example, a removable spacecraft 8 or an object docked to docking station 30, must move in orbit with reduced perigee. Since the upper orbital station 2 has an excess of orbital speed, an object docked to it, for example, a removable cosmetic apparatus 9 or an object docked to the docking unit 31, must move in orbit with an increased apogee. Due to this effect, various objects are docked to orbital stations 1 and 2 with reduced fuel costs for interorbital maneuvers and rendezvous, as well as for launching from the Earth into an intermediate orbit.

 To dock an object being brought out of the Earth with the lower orbital station 1, this object is put into orbit, whose height at the apogee is equal to the height of the orbit of the lower orbital station 1, and the height at the perigee is 3 times lower than the distance between the orbital stations 1 and 2. For docking with the lower orbital Station 1 of an object moving in a lower orbit, this object is transferred to a new orbit with the above parameters. Docking is carried out at the apogee point of the object with a zero speed of meeting from the lower orbital station 1 to the base unit 6 as a removable spacecraft 8 or to the docking station 30. For docking with the upper orbital station 2 an object moving in a higher orbit, this object is transferred into orbit , whose height at the perigee is equal to the orbit height of the upper orbital station 2, and the height at the apogee above it is 3 distances between the orbital stations. Docking is carried out at the point of perigee of the object with a zero speed of meeting with the upper orbital station 2 to the base unit 7 as a replaceable cosmetic device 9 or to the docking station 31. The fuel consumption during such operations is less than during normal operations of putting into orbit, rendezvous and docking .

 When docking various objects (modules, ships, etc.) with tethered docking modules 16 and 17 with tethered cables 14 and 15 released at zero counter speed, the corresponding increase in perigee or decrease in the apogee of the docked object should be even greater than with at the junctions with orbital stations 1 and 2. Due to this effect, various objects are docked to orbital stations 1 and 2 with significantly lower fuel costs for interorbital maneuvers and approach, as well as for removal from Зе Does the intermediate orbit.

 For docking of an object brought from the Earth to the lower bound orbital station 1, docking module 18 is diverted on a tethered cable 14, produced by the mooring winch mechanism 22, the docked object is brought out of the Earth into orbit, whose height at the apogee is equal to the height of the orbit of the assigned tethered docking module 16 and height perigee below it at 6 distances from the tethered docking module 16 to the center of mass of the complex. The docking is carried out at the apogee point of the object with a zero speed of encounter with the tethered docking module 16, after which the tethered docking module 16 together with the object docked as a towed spacecraft 18 is pulled to the lower orbital station 1 on the tethered cable 14, retracted by the mooring winch mechanism 22, and it is docked to the base unit 6 using the mechanism of re-docking 32. Similarly, docking with the lower orbital station 1 of the object located in the lower orbit is carried out. For docking with an upper orbit object 2 to the upper orbital station, the tethered docking module 17 is retracted on the tethered cable 15, released by the mooring winch mechanism 23, the object is transferred from its orbit into the orbit, the height of which at perigee is equal to the orbit height of the assigned tethered docking module 17 , and the height at the apogee above it is 6 distances from the attached docking module 17 to the center of mass of the complex. The docking is carried out at the re-point of the object with a zero speed of meeting with the tethered docking module 17, after which the tethered docking module 17 together with the object docked as a towed cosmetic device 19 is pulled to the upper orbital station 2 on the tethered cable 15, retracted by the mooring winch mechanism 23, and flips onto the base unit 7 as a replaceable cosmetic apparatus 9 using the flip mechanism 33.

 When the deployed complex moves in the Earth’s magnetic field between the ends of cables 5, a natural potential difference occurs, reaching values of about 200 B per kilometer of cable length 5. When collecting or collecting electric charges with the end of cables 5 into the ionospheric plasma using electric contacts 28 and 29 through the cables 5 an electric current flows, the interaction of which with the Earth's magnetic field leads to inhibition of the orbital motion of the complex by ampere forces. When creating, for example, using an onboard electric generator at the ends of cables 5 an artificial potential difference opposite in direction to the natural potential difference and exceeding it in magnitude, reverse electric current flows through cables 5, the interaction of which with the Earth’s magnetic field accelerates the orbital motion of the complex by ampere forces. When passing through the cables 5 of an alternating electric current, electromagnetic waves are emitted. Due to these effects, electricity is generated on board the complex, electrodynamic maintenance or increase of the complex’s orbit, and effective emission of radio waves. As onboard power generators, for example, power modules docked to docking units 30 and 31 can be used.

 To obtain electricity on board the complex, electrical contactors 28 and 29 collect or discharge into the ionospheric plasma electric charges accumulating due to the interaction of cables 5 with the Earth’s magnetic field at the ends of cables 5. The electric current generated in the cables 5 is used, for example, to charge the batteries or is disposed of in another way. In this case, the orbit of the complex decreases due to its inhibition by ampere forces. To electrodynamically maintain or increase the orbit of the complex using, for example, on-board electric generators, an inverse potential difference is created between the ends of the cables 5, and the electrical contactors 28 and 29 collect or discharge electric charges into the ionospheric plasma. In this case, a reverse electric current is generated in cable 6 and increases due to the acceleration by the ampere forces of the complex orbit. To emit radio waves using, for example, on-board electric generators and electric contactors 28 and 29, alternating electric current is generated in the cables 5; in this way, for example, global radio communications in the low frequency ranges can be implemented.

Claims (3)

 1. A long-term manned orbital cable system comprising two modular orbital stations with base units and docking spacecraft connected by several cables, and a towed spacecraft connected by a tethered cable from one of the orbital stations, characterized in that one of the cables is made of the main power and the rest are adjusting, each orbital station contains an aggregate-mounting module docked to the base unit, the first aggregate-mounting module is equipped with a main m with a winch mechanism for releasing and retracting the main power cable, which is wound from one end on the drum of the main winch mechanism, and at the other end is fixed to the second assembly-mounting module, the second assembly-mounting module is equipped with an adjustment winch mechanism for releasing and retracting the adjustment cables, moreover, the adjustment cables from one end are wound on the drum of the adjusting winch mechanism, and the other ends are fixed on the first assembly-mounting module.  2. The complex according to claim 1, characterized in that it contains lengthy electric cables, and the assembly and installation modules contain trusses on which the docking units, electric plasma contactors and cable winch mechanisms for releasing and retracting the lengthy cables wound on the drums are made, the ends of each cable are wound on the reels of cable winch mechanisms made on trusses of the opposite assembly and assembly modules and are electrically connected to the contactors.  3. The complex according to claim 1 or 2, characterized in that at least one orbital station comprises a berthing module docked to the base unit and a tethered docking module connected to the berth module by a tethered cable; a mooring winch mechanism is placed inside the berth module for releasing and pulling the winding cable from one end onto the drum, the other end of which is fixed to the tethered docking module, and the towed spacecraft is docked to the tethered docking module, and and the mooring module, a mechanism for re-docking the spacecraft from the tethered docking module to the base unit and vice versa was made.