RU2621805C2 - Vehicle for interplanetary communication (versions) - Google Patents

Abstract

FIELD: transportation.

SUBSTANCE: group of inventions refers primarily to the man-rated vehicles for flights in the middle and outer space. On the vehicle framework there are modules of controlled aerostatic floatability, electric motors with screw propellers, liquid jet engines with fuel and oxidizer capacities, as well as the power supply and the traffic control systems, inhabited and technical compartments, ports for space vehicles approaching, thermal protection facilities for the inhabited compartment and vehicle equipment. The modules floatability is provided by pumping from the technical compartment tanks of the liquid helium and its gasification under the dome structures of these modules (the inverse process is also provided). The support for the missile with payload location can be installed on the vehicle, launched or descended from the space orbit.

EFFECT: extension of the vehicle of this assignment functionality.

5 cl, 13 dwg

Description

The invention relates to vehicles for interplanetary communication and can be used in the construction of spacecraft.

Known spacecraft (SC) and their groups (space stations - CS), operating in near-Earth and higher orbits. The launch of such spacecraft is carried out using powerful ground-based complexes (cosmodromes) and multi-stage launch vehicles of single use. At the same time, it is not the SC itself that returns to Earth, but only its module - the descent capsule. A ballistic trajectory is used for descent, which is associated with large overloads experienced by crew members and thermal overheating. The need to use a ballistic trajectory is explained by the lack of a resource on the spacecraft for braking during descent due to the limitation of the payload weight at launch.

Known rocket for interplanetary flights, comprising a central module of the first stage with side modules of the first stage and a central module of the second stage with side modules of the second stage, the side modules are connected to the central connecting rods that can be undocked, while all modules have a housing, oxidizer and fuel tanks inside the housings and at least one liquid rocket engine in each module, and a system for transferring one of the fuel components from the side modules to the central one. The missile also includes roll nozzle blocks containing two opposed roll nozzles. The roll nozzle blocks are mounted on the outer surface of the housing of the side modules of all stages remote from the launch vehicle axis (RF patent No. 2464207, IPC B64G 1/40, B64C 29/04, 2012 publication).

A spacecraft is known that contains experimental modules, comprising modules a ring-shaped truss frame with fastening elements of the modules from its inner edge, solar batteries and radiators of the thermal system, as well as orientation system engines, connected to the outer edge of the frame. The apparatus contains a module located in the center of the ring of the frame, at least some experimental modules are connected to the specified module with their own ends using docking nodes, and other ends with the inner face of the frame, solar panels and radiators of the thermal management system are placed in the plane of the ring frame, and orientation system engines are installed on the side surfaces of the experimental modules near their ends connected to the frame (RF patent No. 2072951, IPC B64G 1/10, 1997 publication).

Known devices do not provide the ability to launch and launch rockets from space orbits, that is, create a “space elevator” to launch reusable inhabited descent orbital stations.

As the closest analogue, a vehicle (TS) of increased carrying capacity was accepted according to the application No. 2015107430/11 of 03/04/2015.

The specified vehicle with increased capacity for high-pressure air includes a transporting module and a transportable module connected to it via a connection unit, while the vehicle uses Archimedean force and engines with various types of propulsors as propellers. The transport module of the vehicle is made in the form of a mobile launch pad, and the transported module of the vehicle is a launch facility containing a base made in the form of an ellipse with several groups of shells of constant and variable volume located along its perimeter, equipped with buoyancy control systems including liquid helium reserves and equipment for its reverse pumping, electric motors equipped with recharge systems x batteries from renewable energy sources on flowing electric generators, motion control and external control systems and devices for moving a vehicle on the ground. The vehicle transport module contains a set of traction electric motors of movement in a horizontal plane at one or several fixed courses and two additional engines for the possibility of correcting a fixed course, as well as traction motors of movement in a vertical plane to fix the position of the transport module in height. The transporting module of the vehicle contains a receiving part, made in the form of a lodgement, and the transported module contains the reciprocal of the connection node of the transporting module with the transported.

However, this universal vehicle is not intended to bring it into outer space, flights and maneuvering in outer space.

The objective of the invention is to create such a configuration of the spacecraft in which it will be able to independently perform a “soft start” with access to a given orbit, maneuver in space (including when performing the function of an interorbital tug) and smoothly return to Earth. The latter is especially important to reduce the overload experienced by the crew and to reduce the overheating of the surfaces of the spacecraft structure itself. The logical completion of the configuration of such a spacecraft can be a modifiable TS of an interplanetary message. And there should be at least two options for modification: a reusable space station (SC) and a space elevator (CL) for launching and launching rockets from space orbits.

The list of applications of such vehicles in any version is limited only by imagination: from the traditional study of near-Earth and near-solar space in a manned or unmanned version (for example, to carry out a research program using several light space shuttle space shuttles), spacecraft transfer from one orbit to another the creation of colonist settlements on the planets of the Solar and, possibly, other systems. For example, the combination “visited space station” + “soft start” can be a very successful commercial project. A start from the polar region of the Earth will help to avoid troubles with the passage of a belt of charged particles at altitudes of more than 600 km.

The vehicle (TS) of interplanetary communication is characterized in that it includes a carcass with a complex of modules of controlled buoyancy placed on it, electric motors with screw propellers, liquid-propellant rocket engines (LRE) with unchanged reactive thrust vectors, energy supply, orientation and control systems, as well as retractable chassis racks, while on the frame there are liquid propellant rocket engines with variable reactive thrust vectors, fuel and oxidizer storage capacities for them, an inhabited compartment with life support systems ports and moorings of spacecraft, the capacity of the fuel supply system’s energy supply, as well as means of thermal protection of the habitable compartment and equipment components of the vehicle, and the inclusion and joint operation of modules, systems and units is carried out both in automatic mode and by command of the pilot or remotely from the center control outside the vehicle.

Controlled buoyancy modules contain dome structures in which fuel and oxidizer storage tanks for LRE are placed, and tanks in each module are designed for only one of the components.

LRE with variable thrust vectors contain stationary trunnions of the rotation mechanisms of the engines themselves, through which the fuel and oxidizer are supplied to the LRE combustion chambers.

Dome designs of controlled buoyancy modules include sections of shells equipped with multi-sector heat-insulating covers and devices for holding the cover sectors in closed and fully open positions.

The energy supply system includes power generation subsystems based on various physical principles, operating alternately or simultaneously in various combinations.

In another embodiment, the vehicle (TS) of interplanetary communication is characterized in that it includes a frame with a set of modules of controlled buoyancy placed on it, electric motors with screw propellers, jet engines (LRE) with unchanged reactive thrust vectors, energy supply systems, orientation and control, as well as retractable landing gear, while a lodgement is mounted on the frame for placing and securing a rocket with a payload launched or lowered from space orbit, and LREs with variable reactive thrust vectors, fuel and oxidizer storage capacities for them, spacecraft mooring ports, energy supply fuel tank capacities, thermal protection means and vehicle equipment elements were also installed, and the inclusion, joint operation of modules, systems and units is carried out as in automatic mode, and on the commands of the pilot or remotely from the control center outside the vehicle.

The invention is expressed in the following set of solutions to achieve the technical result set in the tasks of developing the device of the alleged invention: the total capacity of both the main and backup shells of the modules of controlled buoyancy is sufficient to ensure the lifting of the equipped vehicle into the upper atmosphere; the total power of jet engines is sufficient to bring the vehicle to the calculated orbit, to perform maneuvering in outer space and to decelerate when the vehicle is launched from orbit to Earth; the total fuel and oxidizer capacities are sufficient so that their reserves are guaranteed to ensure the functioning of all jet engines at all stages of the flight program; the total capacity of fuel reserves for energy and life support systems is sufficient to service the crew and its flight program for the entire time from launch from Earth to landing at a predetermined point, including when moving in the atmosphere and using helicopters in emergency situations.

The essence of the proposed solutions is illustrated by the following figures.

In FIG. 1 shows a spacecraft for interplanetary flights; in FIG. 2 is a section AA in FIG. one; in FIG. 3 is a cross section of the BB in FIG. 2; in FIG. 4 is a cross section of an explosive in FIG. 2; in FIG. 5 is a cross section of the GG in FIG. 2; in FIG. 6 - section DD in FIG. 5; in FIG. 7 is a cross-section EE in FIG. 2; in FIG. 8 is a sectional view of LJ in FIG. 2; in FIG. 9 is a cross section of the AI in FIG. 2; in FIG. 10 - shows the layout of the rocket engine on the spacecraft; in FIG. 11 shows a space elevator; in FIG. 12 is a section through a QC in FIG. eleven; in FIG. 13 - layout of the rocket engine on a space elevator.

The proposed vehicle in the embodiment of the reusable orbital space station (CS) contains a rigid frame from the lower 1 (Fig. 2) and upper 2 (Fig. 1, 2) bases connected by couplers 3 (Fig. 1, 10) in the form of pipes. The bases 1 and 2 are structures made of trusses in the form of external and internal closed loops interconnected by radial trusses. All frame elements are made of light alloy. To increase the rigidity of the frame, it is allowed to use cables with pre-tensioning.

On the inner contour of the lower base 1 (Fig. 2), a complex of residential structures 4 (Fig. 1, 2) is rigidly fixed. Under complex 4 is complex 5 (Fig. 2) for technical systems and life support systems, diesel generators for charging batteries with a fuel supply for them, on-board equipment (including systems for technical monitoring of the state of components and systems of the compressor station itself), and other technical needs. On the external contour of the lower base 1 (Fig. 2), the technical compartments 6 are rigidly fixed.

The location of the rooms in the complex 5 and in the compartments 6 is shown in FIG. 7 and 8, where are shown:

a, a '- compartments of diesel generators (atmospheric pressure is maintained),

b, b '- battery compartments,

in, in '- fuel compartments,

g, g '- pump compartments,

d, d '- compressor compartments (atmospheric pressure is maintained),

e, e '- utility compartments,

Well, there are water compartments,

h, z '- compartments for air components,

and, and 'are food storage compartments.

The frame of complex 4 is made in the form of light alloy trusses sheathed with sheet material. The volumes between the outer and inner sheathing sheets are filled with a heat insulator, for example, heat insulator. The outer surfaces are protected by a heat-protective coating, for example, in the form of ceramic tiles. On the roof of complex 4, expandable solar panels can be installed, which are part of the power supply system of the compressor station. In the wall of the complex 4 (Fig. 2) portholes are mounted. Ports for mooring lungs of spacecraft (not shown conditionally) are mounted on the lower base.

On the inner contour of the lower base 1 (Fig. 2) and the upper base 2 (Fig. 2), pylon rings 7 (Fig. 2, 3) of truss structures are rigidly fixed. Inside the lower pylon ring 7 (Fig. 2), using rigid suspensions 8 (Fig. 2, 3), a group of accelerating liquid-propellant jet engines 9 (Fig. 2, 3, 10) was installed, and screw ends were screwed at diametrically opposite points at the ends of the pylon rings throttling engines 10 (Fig. 2, 9, 10) with electric drives used when maneuvering a CS in the atmosphere in a horizontal plane.

On the outer contour of the lower base 1, dome structures 11 (Fig. 1, 2) are rigidly fixed, formed by rigid profiles 12 (Fig. 5, 6), strips 13 (Fig. 5, 6) of titanium. In the lower parts 14 and 15 of the dome structures 11 (Fig. 1, 2) there are rigid compartments of the fuel tanks and the oxidizer of jet engines installed on the lower base 1 (in each dome structure there is only one component tank for safe operation), the fuel tank system power supply, equipment compartments 6 modules of controlled buoyancy. In the upper part of the dome structure 11 there are rigid compartments 16, 17 (Fig. 2) of the fuel tanks and oxidizer of liquid-propellant engines installed under the upper base 2 (Fig. 10).

All hard compartments on the outside are equipped with ceramic tiles.

In the middle part of the dome structures 11, sections 18 (Fig. 2, 5, 6) of helium shells, for example, of Kevlar, are placed. Each shell is equipped with an emergency valve (not shown conditionally) to relieve helium overpressure in order to maintain the integrity of the shells themselves. Folded shells occupy the protected lower part of section 19 (Fig. 2, 6) and, when filled with helium, occupy the entire volume of the section. Helium in a liquid state is located in compartments 20 in the lower part of the dome structures 11.

Protection of the shells from above when folded is provided by thermally insulated covers, consisting of sectors 21 (Fig. 5, 6) on the hinges. Sectors 21 (Fig. 5) are held in a fully closed position by means of electromagnetic latches 22 (Fig. 6) mounted on the side surfaces of the protected lower parts of sections 19 (Figs. 2, 5, 6), and in the fully open position using electromagnetic valves 23 (Fig. 6) installed at the required height on the strips 13 (Fig. 5, 6).

The total volume of the sections with helium-filled shells makes it possible to raise the equipped SC to a height of about 20 km.

On the tops of the dome structures 11 (Fig. 2), screw motors with an electric drive 24 (Fig. 2) are installed, which together with the screws 25 (Fig. 2) are protected by caps 26 (Fig. 2), and the power is supplied from the batteries located in equipment compartments 5 and 6 (Fig. 2). The outer contour of the upper base 2 (Fig. 1, 2) serves, inter alia, as a stiffening band for dome structures 11 (Fig. 1, 2). On the outer contour of the lower base 1 (Fig. 2), struts 27 (Fig. 2) of retractable wheeled chassis are also rigidly fixed.

Even with partial compensation of gravity due to Archimedean force, the entire structure can easily move on the wheels of the chassis on the ground.

On the external circuit of the lower base 1 and the upper base 2, liquid-propellant engines 28 (Figs. 1, 10) are used, which are used to compensate for the gravity during braking, and pairwise-mounted liquid-propellant engines 29, 30 (Figs. 10) are used to orient the CS in outer space, and the engines 29, 30 are installed with the possibility of deviation of the main thrust vector from the vertical axis and to create a pair of rotational forces of the SC around the desired axis for its orientation in outer space. The motors 29, 30 can be locked in any position, for example, using a stepper drive. In this case, the pipelines of fuel and oxidizer pass through the fixed axles of the axis of rotation (not shown conditionally).

On radial trusses of the lower base 1 and upper base 2, liquid jet engines 31 are installed (Figs. 1, 10) to ensure the rotation of the COP around the main axis.

On radial farms connecting the inner and outer contours of the upper base 2, liquid-propelled jet engines 32 are rigidly fixed (Figs. 1, 2, 10). Engines 32 are designed for braking when the CS descends from orbit and moves to a smooth landing trajectory.

All the necessary pipelines (fuel, oxidizer) and cable connections, as well as the pipelines of the working fluid - helium, are laid inside the trusses and tubes of the frame (not shown conditionally).

Between the upper and lower bases of the frame 2 and 1 (Fig. 2, 10) there is a passive braking device made of heat-resistant steel, consisting of an intake bowl 33 (Fig. 2, 10) in the form of an annular groove rigidly fixed to the inner contour of the upper base 2 ( Fig. 2, 10), and welded throttle pipes 34 (Fig. 2, 10), fixed in the bottom of the intake bowl 33 (Fig. 2, 10), on the frame trusses of the complex 4 (Fig. 2, 10) and on the inner loop lower base 1 (Fig. 2). Bowl 33 and pipes 34 are lined with ceramic tiles from the inside. Description of the functioning of the COP.

A fully equipped CS has a diameter of about 250 m in plan and has low negative buoyancy due to the helium-filled shells of some sections 18 (Fig. 2). Therefore, the SC can be easily transported to a convenient starting point from the Earth. The start begins with a vertical rise due to the Archimedean force during the gradual filling with helium of the shells in sections 19 (Fig. 2) and 18.

In section 19 of the dome structures 11, compressors pump helium from compartments 20 (Fig. 2), electromagnetic latches 22 (Fig. 6) release sectors 21 (Fig. 5) to lift them with helium-filled Kevlar shells.

In the process of lifting, the CS moves to the calculated point in space orbit using the engines 10 (Fig. 2) of movement in the horizontal plane and is held in it, the electromagnetic valves 23 (Fig. 5) hold sectors 21 of the covers (Fig. 5) in the vertical position, diesel generators in the equipment compartments of the first floor of complex 4 (Fig. 7) recharge the batteries. When moving in a horizontal plane, one or two pairs of engines work: one of the pairs of engines 10 and a pair of jet engines 31 (Fig. 1, 10) in the event that the course does not coincide with the axis of the pair of engines 10.

The change of course is controlled by the command of the pilot or software device by switching pairs of engines 31, the axes of which are closest towards the new course (“rough”) and the necessary “steering” with the help of engines 31, combining the axis of the selected “roughly” pair 10 with the new course by rotating the COP around its vertical axis to the desired side by a small angle (“exactly”), after which the engines 31 are turned off, and the engines 10 operate in the “slow-push” mode (for this, their screws rotate in opposite directions). The use of this technique in two stages minimizes the radius of circulation and the time it takes to maneuver.

Upon reaching the maximum lift height and the calculated starting point, accelerating engines 9 (Fig. 2, 10) turn on with a slow increase in the total traction force, helium is pumped from the shells by compressors back to compartments 20, valves 23 (Fig. 5) release the magnetic bosses of sectors 21 of the covers for closing. The SC is “posted”, which consumes much less fuel and oxidizer than when starting from Earth. Preparation for the launch of the spacecraft into the calculated orbit ends with the operations of turning off the engines 31 and diesel generators for recharging the batteries, winding up and protecting all the shells with sectors 21 (Fig. 5) with fixing their position with latches 22 (Fig. 6). When accelerating engines 9 are turned on at full power, the speed signal required to reach the calculated orbit is reported to the SC.

Maneuvering in space is performed using engines 29, 30, 31 and 9 (Fig. 2, 10), which are also the executive bodies of the coordinate system of the COP. Bringing the compressor to working condition is carried out in a known manner (de-preservation of instruments and equipment, opening solar panels), after which the compressor is ready to carry out the planned program.

For example, to tow a light SC to a new orbit, it is enough to perform the following operations: mooring a light SC to one of the ports of the SC at the calculated point of its orbit; bringing the necessary engines 9 to the required position and turning them on at the calculated point of the flight path for the time necessary for the spacecraft to transition to a new orbit; the descent of the light SC from the spacecraft in a new orbit at the calculated point and the return of the engines 9 to their original position. After completion of all operations, the COP can proceed to the implementation of its program until it is completed. To transfer to the near-solar orbit of the spacecraft, it is enough to give the necessary impulse at the calculated point of the flight path using the accelerating engine 9.

To return to the Earth, the CS needs to go through several stages, at each of which the following operations are performed.

1. Using pairs of engines 29, 30, KS is oriented in space to transition to the lowest possible circular orbit around the Earth due to the operation of brake engines 32 (Fig. 2, 10).

2. At the boundary of the Earth’s atmospheric entry, motors 28 (Fig. 1, 10) turn on and gradually increase traction to compensate for gravity during braking, brake motors 32 gradually reduce traction (at this stage, the passive braking device 33, 34 ( Fig. 1, 2, 9), and when the speed of the CS decreases to about 200 km / h, the CS and seats with pilots are transferred to the position they occupy at start, engines 32, 28, 29, and 30 are turned off, if necessary, after dropping caps 26, the motors 24 are turned on.

3. The accelerating engines 9 (Fig. 2, 10) are turned on for “hanging” the SC at a given height in the atmosphere, the sectors 21 (Fig. 5, 6) are released from holding them with latches 22 and the filling of Kevlar shells with helium begins, while reducing the total the thrust of the engines 9 so that the COP decreases smoothly with a decrease in the rate of decline.

4. When the estimated height above the ground is reached, the CS decrease (it turns out to be “hung out” at a given height), the engines 10 (and 24, if they were turned on) are turned off, the shells are filled with helium, and with the help of engines 10 a horizontal flight to the point of calculated landing .

5. Landing is carried out on the released rack 27 wheeled chassis with the engines 9 turned off by reducing the Archimedean force by pumping helium from the shells back into compartments 20 and compressing it to a liquid state.

When using a vehicle as a “space elevator” (KL) to launch rockets from near-Earth orbit, the KL is based on a frame (Fig. 11, 12), similar to the KS frame (in plan it is not a circle but an oval). The frame is made of bottom 35 and top 36 bases connected by couplers 37 in the form of pipes. On it are mounted, also similar to KS, dome structures 38 (Fig. 11, 12), accelerated liquid-propellant jet engines 39 (Fig. 11) of increased power, liquid-propellant braking motors 40 (Fig. 11, 12), liquid-propellant orientation engines in space 41 and 42 (Fig. 11, 13), liquid-propellant gravity compensation engines 43 (Fig. 11, 13) during braking in the upper atmosphere during descent, screw motors 44, 45, 46 for movement in the atmosphere, struts 47 (FIG. 11) with retractable wheeled chassis. On the inner contour of the lower base 35 (Fig. 12), the lower prism 48 is rigidly mounted with a removable tool tray 49 (Fig. 12) for the rocket 50 (Fig. 11, 12). On the inner circuit of the upper base 36 (Fig. 12), a movable upper latch 51 (Fig. 12) is installed with an electric drive, protected by a casing (not shown). When loading the rocket into the "elevator", the latch 51 (Fig. 12) is in its highest position, and after setting the rocket in the stowed position on the lodgement 49 (Fig. 12), the latch clamps it with a force that prevents the rocket from sliding off the lodgement. The movement of the latch 51 (Fig. 12) is carried out using two pairs of screw-nut, the screws of which 52 (Fig. 12) are synchronously rotated by electric motors 53 (Fig. 12).

An increase in the dimensions of the base of the frame to facilitate the placement of the rocket to an oval shape made it possible to place a larger number of dome structures on the external contours and slightly reduce the overall size of the structure.

Since in this embodiment, fuel for energy and life support systems is not required, the capacities of the hard fuel and oxidizer compartments 54, 55 (Fig. 12) for jet engines in dome structures (Fig. 11, 12) are increased compared to the COP.

Description of the functioning of the CR.

Preparations for the launch, the launch itself, the launch of the spacecraft into the calculated orbit and maneuvering on it are completely similar to operations with the spacecraft. At the calculated point of the orbit by the commands of the control system, the upper latch 51 (Fig. 12) releases the rocket, the marching engines of the rocket itself are turned on and it smoothly leaves the lodgement. The lightweight KL completely repeats the stages of a smooth descent from orbit and a landing of a CS by commands from a control center or control system. For the re-launch, only refueling will be required and, when the caliber of the rocket is changed, the lodgement is replaced.

To receive a rocket in near-earth orbit, the KL is oriented in the necessary way, coordinates its speed relative to the rocket so that the distance between them decreases and at the estimated time clamps the rocket in the lodgement. Smooth descent operations are described above.

Claims (18)

1. Vehicle (TS) interplanetary communication, characterized in that it includes: - a frame with a set of modules of controlled buoyancy placed on it with dome structures; - electric motors with screw propellers; - liquid-propellant engines (LRE) with fixed jet thrust vectors, energy supply, orientation and control systems, as well as retractable landing gear; - the capacity of the fuel and oxidizer for rocket engines; - inhabited compartment with life support systems and mooring ports of spacecraft; - capacity of fuel reserves of the energy supply system; - means of thermal protection of the habitable compartment and vehicle equipment elements; - modules of controlled buoyancy are made with the possibility of changing the buoyancy of the vehicle (negative or zero or positive) due to the pumping of helium, which is in a liquid state in tanks located in technical rooms under the dome structures of modules of controlled buoyancy, both in the shell of dome structures and back to the helium storage tanks, while compressing the gaseous helium again to a liquid state by means of compressors; - electric motors with screw propellers, which provide both horizontal movement in the atmosphere of the planet and movement of the vehicle on the planet’s surface on the wheels of the chassis of retractable vehicle racks, provided that it is negatively buoyant; - LRE with unchanged vectors of reactive thrust, used both as booster and brake engines when landing a vehicle, and thrust vectors of booster LRE and brake LRE are directed towards each other and operate alternately, while LRE with unchanged vectors of jet thrust are used in vehicles as supporting a vehicle in a horizontal position when it brakes in the atmosphere of the planet, so that the jet thrust vector of these engines is directed perpendicular to rhnosti planet; - two pairs of rocket engines with variable reactive thrust vectors installed on the frame of the vehicle and containing stationary trunnions of the rotation mechanisms of the engines themselves, through which the fuel and oxidizer are fed into the combustion chambers of the indicated rocket engines, - a passive braking system to reduce speed in the atmosphere of the planet, placed on the frame of the vehicle above the inhabited compartment and consisting of a intake bowl having thermal insulation from ceramic tiles, and welded throttle pipes diverging from this bowl, also lined with ceramic tiles, at the same time, the inclusion and joint operation of modules, systems and units is carried out both in automatic mode, and on the instructions of the pilot or remotely from the control center outside the vehicle. 2. The vehicle according to claim 1, characterized in that the capacities of the fuel and oxidizer reserves for the liquid propellant rocket engines are located in the dome structures of the modules for controlled buoyancy, and the containers in each module are designed for only one of the components. 3. The vehicle according to claim 2, characterized in that the domed designs of the modules of controlled buoyancy include sections of shells equipped with multi-sector heat-insulating covers and devices for holding the sectors of covers in closed and fully open positions. 4. The vehicle according to claim 1, characterized in that the energy supply system includes power generation subsystems based on various physical principles, operating alternately or simultaneously in various combinations. 5. The vehicle according to claim 1, characterized in that a lodgement is mounted on the frame for placing and securing a rocket with a payload launched or launched from space orbit.

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