WO2014021744A2 - Method for putting ring-shaped and grid-like surfaces into outer space and a device for implementing same - Google Patents

Description

 A method of launching into space annular and lattice surfaces and a device for its implementation.

The field of technology.

The invention relates to the field of astronautics, and in particular to means of delivery of payloads into space and their return. The invention can be useful in the industry of tourist orbital hotels, in particular large, with a diameter of more than 100 meters, toroidal space stations with artificial gravity, for space cruises without service ships (tourists are in the luxury cabins of the ring station when starting into orbit and when it returns) astronomical stations, in the construction of large optical and radio telescopes, large phased arrays for various radio engineering tasks, truss structures, as well as for the delivery of large areas her mesh designs, designs in the form of blinds, etc.

The prior art.

The prior art method of launching into space with the return of reusable spacecraft with orbital payload having aerodynamic planes. (Space Shuttle,) The Shuttle's cargo compartment is not enough to launch oversized cargo into space and return to earth (a planet with an atmosphere). Also known are devices of rocket systems equipped with descent capsules of the Soyuz or Apollo type, which use rocket blocks mounted vertically in tandem and in a batch scheme for launching into space, in which the height of the rocket system significantly exceeds its midship area, which creates significant longitudinal mass overloads. This device does not provide output into space of oversized structures of considerable size and complex configuration and also requires complex launch complexes and weighting of rocket structures stages due to the large column of fuel weight at the bottom of the fuel tanks where the ratio of the height of the fuel level to the area of the base onto which it presses exceeds 1 huge acoustic and vibration loads from high power rocket engines concentrated in one place. Which limits the size of the missile systems and therefore the weight of the displayed cargo. Also, such systems cannot start from unprepared launching sites, for example, from the water surface due to the lack of stability of the rocket system. There is also a method and device for moving space-sensitive mass cargoes of patent RU 2159197 C2 where there are many the lattice surfaces are formed by beams or trusses while the transported cargo is fixed on slings at one point and rocket engines and fuel tanks are concentrated on the nodes of the joints of these beams, which restricts the launch into space of cargo since it is overweight as trusses and beams and concentrated in rocket nodes engines and tanks with fuel, as well as this method does not provide the output themselves lattice or ring structures. The aim of the present invention is to eliminate these drawbacks, due to the uniform distribution of engine thrust on a lattice or ring structure and steps designed for its output into space, and plans for such steps (trusses and beams) are made in the form of tanks with fuel.

SUMMARY OF THE INVENTION

The invention is aimed at expanding the functionality and increasing the efficiency of launching space objects of significant size and complex configuration in one launch, without using the principles of folding-deployment, as well as without expensive and busy operations of rapprochement, docking, installation of modular assembly in space of objects that are impossible entirely put in the cargo compartments of existing carrier rockets ..

The solution to this problem is ensured by the fact that in the method of launching into space the annular and lattice surfaces equipped with a rocket carrier representing a set of stages consisting of fuel tanks and rocket engines, according to the invention, an object (payload) that is launched into space without folding and without crushing into separate modules are entirely placed on rocket blocks (steps) repeating the form (plans) of the output cargo, made and interconnected according to the silhouette or close to the silhouette its configuration. In this case, the entire missile system takes the form of an annular or lattice surface, which is launched into space by a conventional plane to the flow or a conventional edge of this plane. It is possible that annular or lattice surfaces were delivered and returned from space using aerodynamic drag by the atmosphere of the planet by pulling (filling) the empty space between the planes with membranes in the form of elastic membranes made of heat-resistant foil or film or fabric. Or return the cargo using its natural form with the effect of a lattice or annular wing or a simple flat surface in case the space between the planes is tightened with membranes. In this case, in the first case, the plane of the annular or lattice surface is perpendicular to the flow; in the second case, the plane has an edge to the flow with the required angle of attack. The fuel level in the tanks of the silhouette steps for the output of the payload (annular or trellised surface) as well as traction, vibration and acoustic loads are distributed evenly on the edges of the ring, truss, the lattice plane, according to the integration of its width and local mass, and in the space-launching or space-returning section, the entire plane can be rotated to create centrifugal forces to give rigidity and aeroelastic stability to the entire system. In addition, to ensure the best characteristics of the stages (structural perfection) in the annular and lattice cargo output device, the fuel tanks are made in a cross-section of a figured shape, in which their lateral surface is part of the nozzle (central body) while the rocket engines are located in the upper part of the stages with a linear by the location of the chambers, the outflowing gases wash part of the stage by heating the fuel through the shell, which, when expanding, provides self-charging of the fuel tank, while automatically cooling of the shell of the side surface of the step occurs.

 The oversized space object in the form of, for example, an annular orbital station, of significant size or lattice surface, shutters, trusses, in the form of a flat or convex concave or biconvex shape, is placed by a plane, horizontally on steps with fuel tanks and rocket engines, which repeat the silhouette configuration in projection (form) of the payload (output object), while the individual composite power elements of this configuration are Ribs, beams or the rim of the output object (payload e) give a separate aerodynamic shape or provide a separate fairing, which also has in its basis a silhouette similarity of the displayed object. Silhouette steps have a tandem in the form of layers or conditional planes having a silhouette projection width and a height (thickness) that characterizes the volume of the fuel capacity of the stage. At the same time, the thrust of the engines on the silhouette steps is distributed in such a way as to ensure uniform distribution of thrust and acoustic loads from the working engines, placing them at a maximum distance from each other with a large number of small thrusts, according to the silhouette of the load, according to the concentration of masses at different points of the payload according to its configuration (form) A, the object is returned by atmospheric braking and planning, using the effects of the trellised wing for the trellised payload and the ring clan for tsevogo. It is possible to increase the steps in the horizontal plane by attaching them to the payload, so that the horizontally lying fuel tanks are the edges of the grid, while the fuel tanks are given an aerodynamic shape. The payload has a rocket engine with a thrust exceeding its weight. And each horizontally lying step is equipped with rocket engines with a thrust corresponding to their weight. The steps are connected by their ends to each other, rigidly or articulated in plan, forming force triangles — the edges of the lattice. The connection nodes of the steps have fuel connections between each other for the mutual distribution of fuel, and the separation of the steps occurs by discarding the fuel blocks (grid edges) from the periphery to the center while

s fuel is pumped into tanks that are located closer to the center and are attached to the payload, the second part is consumed by the donor stage engines.

 It is possible that the fuel tanks that form the edges of the lattice should be streamlined in the form of a bearing profile in cross sections that create a lifting force similar to a lattice wing, and to create elastic stability of the shape of ring or lattice objects at the stage of removal or descent in the atmosphere, their plane is twisted around the center of mass at the same time, centrifugal forces create the necessary stresses in the structure increasing its rigidity and forming the correct form of the bundle, while the peripheral worked out steps are discarded by m In this case, there can be as many steps as you like, and the payload weight is limited only by the thrust of the main engine, which can exceed the load weight sufficient for a given accelerated lift, for example, 1.5 - 2 times, while the rest of the engines work only for lifting a bunch of steps carrying fuel for its operation. Thus, the peripheral stages work by feeding their own engines and pump up the capacities of the steps located closer to the center (the capacities of the periphery steps consume fuel much faster than the central ones) while at the same time rapidly losing weight the peripheral steps proportionally reduce the engine thrust in such a way as to maintain the correct common plane systems (bundles).

It is possible that the silhouette steps were fragmented into separate fuel modules (were composite) while discarding them as fuel consumption, in the sequence in which the balance of the annular or trellised surface is maintained by the balance of the thrust of rocket engines.

You can connect silhouette (ring) steps to each other with an oblique junction (“on the whisker”) at which the fuel tanks in cross section are given such a circuit that one of the walls of the fuel tank is part of the nozzle (central body) organizing the outflow from the rocket engine chambers, and when flowing around the side surface of the stage with a hot stream of a jet stream, heat is transferred through the fuel tank shell to the fuel, which expands and creates a pressure inside it, which is used to pressurize it, while vtomaticheski, cooling most of the fuel tank wall.

Moreover, in the device for launching oversized objects into space during operation and return to the planet, the space between the ring or lattice plans of the load is tightened with membranes, which are used as reflex surfaces for reflection in the optical and radio ranges. When folded, the membranes are placed under the fairings in rolls or bobbins on the plans, as well as at the nodes of their intersections (joints) and after delivery into space with the help of halyards fixed at one end on the membrane box with the other end on the opposite beam of the plan. By shortening the length of the halyard, the scaffold of the membrane wound off a roll or bobbin is attracted to to the opposite plan and fasten with the necessary tension and, if necessary, with sealing. The membranes can be tightened both on one side of the plane and on the other, lattice structures in the form of blinds can be launched into space, while during the start from the ground, the plane of the blinds is oriented with ribs to the stream, while during the return from space the blinds are closed and used a solid plane for aerodynamic drag and planning, it is possible to use the planes of the blinds as a lattice wing; in addition, the delivery to space of flexible lattice structures or grids drawn by a membrane from the planet’s surface is possible They use thermal expansion and aerostatic lifting force as well as a large-area bottom effect, for which a membrane structure equipped with a frame is spread on the surface of the planet, and the engines are distributed under the surface of the membrane on the frame nodes that include when lifting the structure, while the jets from rocket engines are pumped under the membrane hot gas with temperature tl which creates aerostatic lifting force Fst along with reactive force Fr, and when lifting the structure, engine thrust and eyelids the torus of their thrust is distributed on the membrane in such a way that the shell structure is formed in the form of a convex concave surface, for example, a hemisphere in which the working fluid flowing out of rocket engines creates a heat bubble with pressure Pg flowing out of the created structure creating additional lifting force Fg thus ensuring the equality F = Fst + Fri-Fb + Fg, it is possible to use another additional lifting force Fb - Bernoulli forces arising from lateral air blowing of the structure when it is lifted.

A brief description of the drawings.

In FIG. 1. Schematically presents a method of launching into space a ring-shaped cargo, for example, an annular orbital station in its entirety (with a ring plan) and with radial rays and mass concentrations in different parts.

 In FIG. 2. Various variants of the method and arrangement of rocket stages with engines for launching an object into the space of an annular lattice and lattice honeycomb form, for example, annular space stations, cells of large orbital telescopes, phase gratings, parabolic power structures, blinds, or giant toroidal building elements, are presented schematically. habitable stations.

In FIG. 3. Scheme of the reusable method for launching into space and returning spent steps and loads to the ground in a ring and trellised form in the trellised wing and ring-wing mode, for example, when assembling or disassembling a large orbital ring station Figure 4. General view of the method of connecting missile stages "on the whisker" to increase the structural perfection of the stages and characteristics of the expiration of a jet stream with automatic pressurization of fuel tanks and cooling their shell in contact with a hot jet stream

 5. A method is shown for tightening the interplanar space of lattice surfaces with membranes to create reflective surfaces in space, for example, for parabolic reflectors and also aerodynamic surfaces when returning from space.

 In Fig.6. Schematically shows a method of modular placement and rejection of steps on the silhouette plans of an annular or lattice surface.

 In FIG. 7 A method for connecting missile stages into a flat bundle of unlimited area and discarding them as they are used is shown.

 In FIG. 8 The application of a method for the withdrawal or landing of cargoes of complex configuration is shown, for example, delivery to space or landing on a celestial body of complete orbital stations (for example, ISS take-off and landing on the moon, asteroids, Phobos, Deimos, etc.).

 In FIG. 9 A method is shown for launching space-borne ring payloads using standard launch vehicles.

In FIG. 10 The application of the method for the delivery of space blinds is shown. 11 shows a method for delivering into space flexible lattice structures or grids behind a membrane drawn from the surface of the planet using thermal expansion and aerostatic lifting force as well as a large bottom effect.

EMBODIMENTS FOR CARRYING OUT THE INVENTION.

A method and apparatus for launching cargo 1 with an annular or lattice surface (FIG. 1), for example, an annular orbital station or beam structure for mounting reflective surfaces or trusses for various space structures of significant dimensions, contains at least two detachable accelerating stages 3 and 4, and one last stage 5 which is part of the space structure, the first stage 3 consisting of a fuel tank and engines. The steps are repeated in terms of the shape of the rings or gratings of the output cargo 1 and the connection layers are end portions. Engines 2 are located in the lower end part of the steps. Moreover, the contour of the plans of annular or lattice surfaces (Fig. 2) may have various options from concentric annular with radial plans to honeycomb frames. In addition, it is possible to use the plans of the rocket system (Fig. 3) for the withdrawal of goods, the return of steps or the return of the cargo itself from space in the mode of trellised wings or ring-wings. Which is very important with a large number of starts, for example, if the ring or

b the lattice cargo is a composite structural element of the cross section of a toroidal orbital station of significant dimensions or of any structure on the surface of the celestial body A to increase the structural perfection of the steps, simplify and provide better conditions for the outflow from the rocket engines of the working fluid 8 (Figure 4) to the side of the fuel tanks give a curved concave bend with a contour in cross section corresponding to the contour of a half-nozzle or “central body” 7 which is a shell th capacity, and rocket engines 2 are located in the upper part of the stage, for example with a linear arrangement of combustion chambers. At the same time, the wall of the tank shell heated on one side by the expiring working fluid is cooled on the other hand by the fuel components, and the expansion pressure of the fuel components during this process is used to pressurize the fuel tank itself. Moreover, the steps are connected by an oblique joint in which the upper part of the lower stage 3 repeats the contour of the lower part of the upper stage 4, etc.

 In addition, it is possible to save the steps and return the displayed cargo 1 from space by tightening the empty areas between the planes with membranes 9 (Fig. 5) which are stored in the folded-up active section of the flight in streamlined compartments 6 on special coils in the nodes of the lattice or on its plans ( ribs) and straighten, tightening the spaces between the planes to create reflective surfaces in space and to enter the atmosphere with aerodynamic quality, when returning, and if the distance delta 2 significantly exceeds delta 1 Figure 5 then When gas is supplied between the upper and lower shells 9, a segmental conical capsule is formed, while a significant reduction in the specific load on the capsule with a load of less than 10 kg / sq. m is achieved.

It is also possible to perform steps 3, 4, 5 and more n, in the form of separate modules of a spherical or oblong cylindrical shape (Fig. 6) which are fixed under a payload 1 repeating its silhouette plan and discarded as the working fluid 8 is developed in this order to ensure the balance of the entire structure with respect to the center of mass and the center of pressure, and to create elastic stability of the rocket system of a significant size and preserve its plane, the system is twisted in this plane to create uniform centrifugal loading silts. At the same time, the Central Bank forces are also used to discard the silhouette plans of the modular steps 3 and 4. The steps can also be interconnected to form lattice planes composed of conditional beam capacitances forming power triangles. Fig. 7 for this stage is made in the form of elongated tanks whose ends provide connecting nodes 10 which also have pneumohydraulic connectors for active fuel transfer (redistribution) between the tanks. The lateral part of the tanks directed towards the oncoming flow is given an aerodynamic shape or equipped with a fairing 6 with such a scheme for the formation of steps, it is convenient to deliver them to the starting point of the railway or by motor transport. In this case, there can be as many steps as you like, and the payload weight can be limited only by the thrust of the marching engine which will not exceed the weight of the load by 2-3 times, i.e. more than 500 tons, for example, when using rocket engines such as RD-170. The rest of the engines operate only to lift the network from the stages carrying fuel for its operation. At the same time, on the engines of the first stages located on the periphery of the bundle, as the amount of fuel decreases, thrust is reduced by compensating for the weight of the step so that the conditional plane of the bundle of steps and payload retains the correct (given) shape. The method of launching into space also allows performing the reverse operation, i.e., soft landing on a planet or an asteroid, Fig. 8 At the same time, the payload can be a rather complicated configuration, for example, a large orbital station in full assembly (ISS) or a lunar base which is equipped with modules forming steps in silhouette. In addition, payloads, for example in the form of an annular shape, can be fixed on the external slider directly to the finished standard launch vehicle of Fig. 9. while for unloading and road stability of the payload, auxiliary thrust and control engines are fixed on it. To output structures in the form of blinds FIG. 10 use combined modular steps, delivery into space of flexible lattice structures or meshes tightened by a membrane from the planet surface. 11 is carried out using thermal expansion and aerostatic lifting force as well as a large bottom effect, for which a membrane structure equipped with a frame is placed on the planet surface and engines distributed under the surface of the membrane on the nodes of the frame that include when lifting the structure. while the jets from rocket engines inject hot gas under the membrane with a temperature tl which creates aerostatic lifting force Fst along with the reactive force Fr, and when lifting the structure, the engine thrust and their thrust vector are distributed on the membrane so that the shell structure forms in the form of a convex surface for example, hemispheres in which the working fluid flowing out of rocket engines created a heat bubble with pressure Pg flowing out of the created structure creating an additional In this way, ensuring the equality F = Fst + Fr + Fb + Fg, it is possible to use one more additional lifting force Fb - the Bernoulli force arising from lateral air blowing of the structure when it is lifted.

LITERATURE.

 Joint venture Uman boosters. Cosmodromes. M., Restart 2001 Publishing House - 216 p.

C. Gatland. Rocket and Space Technology. Ed. Peace.

Claims

A method for launching ring and lattice surfaces into space and a device for its implementation. Claim. 1. The method of launching into space ring and lattice surfaces equipped with stages in the form of containers with fuel and rocket engines for acceleration at the launch site, as well as parachutes or wings at the site of descent to a planet with an atmosphere, differs in that the launched oversized space object in the form of, for example, a ring an orbital station of significant size or a lattice surface in the form of a flat or convex concave or biconvex shape formed by truss ribs is placed flat, horizontally on stages with fuel tanks and rocket engines, which repeat in the projection the silhouette configuration (shape) of the payload (launched object) , in this case, the individual composite power elements of such a configuration - the ribs, beams or rim of the launch object (payload) - are given a separate aerodynamic shape or equipped with separate fairings, which also have at their base a silhouette similarity to the launch object, while the silhouette stages are arranged in tandem in the form of layers or conditional planes having the width of the silhouette projection and the height (thickness) which characterizes the volume of the fuel capacity of the stage, while the thrust of the engines on the silhouette stages is distributed in such a way as to ensure uniform distribution of thrust and acoustic loads from operating engines, with a large number of them but low thrust, having them at the maximum distance from each other, according to the silhouette of the launched load, according to the concentration of masses at various points of the payload according to its configuration (shape), and return the object by braking the atmosphere and planning, using the effects of a lattice wing for a lattice payload and a ring glider for an annular one. 2. The method according to claim 1 differs in that the stages are built up in a horizontal plane by attaching them to the payload, so that the horizontally lying fuel tanks are the ribs of a flat lattice, while the fuel tanks are given an aerodynamic shape, the payload has a rocket engine thrust exceeding its weight, and each horizontally lying stage is equipped with rocket engines with thrust with the same ratio to their weight, the stages are connected by their ends to each other, rigidly or hinged in plan forming power triangles - lattice ribs, the connection nodes of the stages have fuel connections among themselves for mutual distribution fuel, and the separation of stages occurs by discarding fuel blocks (grid ribs) from the periphery to the center, while part of the fuel from the tanks of the peripheral stages is constantly pumped into tanks that are located closer to the center and attached to the payload, while the peripheral stages in front of the separation consume fuel faster stages located closer to the center while simultaneously reducing engine thrust to maintain the plane of the overall bundle, while the peripheral spent stages are discarded as fuel is consumed, in addition, for additional gyro-stabilization of such a flat rocket bundle, it is possible to spin it with the entire plane relative to the center of mass, while there may be stages as much as you like, and the weight of the payload can be limited only by the thrust of the main engine, which will not exceed the weight of the cargo by 2-3 times, and the remaining engines work only to lift the network of stages carrying fuel for its operation. 3. The method according to claim 2 differs in that the fuel tanks forming the lattice ribs are streamlined in the form of a supporting profile in cross-section that creates lift like a lattice wing. 4. The method according to claim 1 differs in that to create elastic stability of the shape of ring or lattice objects at the stage of ascent or descent into the atmosphere, their plane is twisted around the center of mass while centrifugal forces create the necessary stresses in the structure, increasing its rigidity and forming the correct shape 5. The method according to claim 1 differs in that the silhouette stages are crushed into separate modules (made composite) and discarded as fuel is consumed, in a sequence in which the balance of the annular or lattice surface is maintained by the balance of the thrust of the rocket engines; in addition, it is possible to divide the most useful loads on individual fragments equipped with rescue systems, for example in an emergency. 6. The method according to claim 1 differs in that the stages are connected to each other by an oblique joint (“on the miter”), in which the fuel tanks in cross section are given such a contour that one of the walls of the fuel tank is part of the nozzle (central body) that organizes the outflow from the chambers rocket engines, and when the hot jet stream flows around the side surface of the stage, heat is transferred through the shell of the fuel tank to the fuel, which expands and creates pressure inside it, which is used to inflate it, while the wall of the fuel tank itself is automatically cooled. 7. The method according to claim 1 differs in that after the launch of oversized objects into space, the space between the annular or lattice cargo planes is covered with soft membranes, or blinds, which are used as reflective surfaces for reflection in the optical and radio ranges; when folded, the membranes are placed under the fairings on the plans, as well as at the nodes of their intersections (connections), and the blinds are oriented edge-on to the flow, and after delivery into space using Yu halyards fixed at one end to the luff of the membrane with the other end on the opposite beam of the plan, by reducing the length of the halyard, the luff of the membrane is pulled to the opposite plan and secured with the necessary tension and, if necessary, with sealing, the membranes can be tightened both on one side of the plane and on the other, in this case, the planes of the blinds are simply oriented in the desired way using drives. 8 The method according to claim 1 differs in that the payload is made in the form of a segment (open cylinder) of a large toroidal station, while the end parts of the segment are left open for the free passage of the oncoming flow, and all segment bulkheads are oriented edge-on to the flow. 9. The method according to claim 8 differs in that the delivery into space of flexible lattice structures or meshes covered with a membrane from the surface of the planet is carried out using thermal expansion and aerostatic lift, as well as the bottom effect of a large area, for which a membrane structure equipped with a frame is spread on the surface of the planet Moreover, the engines are distributed under the surface of the membrane on the frame nodes, which are turned on when the structure is lifted, while jets from rocket engines pump hot gas with a temperature tl under the membrane, which creates an aerostatic lift force Fst along with the reactive force Fr, and when the structure is lifted, the thrust of the engines and their thrust vector , are distributed on the membrane in such a way that a shell structure is formed in the form of a convex-concave surface, for example a hemisphere, in which the working fluid flowing from the rocket engines creates a heat bubble with pressure Pg flowing from the created structure creating an additional lifting force Fg thus ensuring the equality F=Fst+Frl- Fb+Fg, it is possible to use another additional lifting force Fb - the Bernoulli force that occurs when the wind blows the structure sideways when it is lifted. 10. A device for implementing the method according to claim 1, characterized in that the annular surface is made in the form of a sealed hollow torus forming a habitable space station with artificial gravity, inside which household and technical compartments are located, radial rays made of hollow fuel pipes converge to the center of the ring containers, the number of which is selected at least three, inside of which, after emptying the containers, there are tunnels for moving people and goods to the center of the station, while the beams are hermetically connected to a central sealed cylindrical module with a streamlined end part, a ring with radial beams is placed on hollow annular stages with radial tubular beams forming fuel tanks, wherein the number of stages is chosen to be at least three; rocket engines according to the local distribution of mass projection along the surface launched into space. 11. The device according to claim 9 is characterized in that the ring is made in cross-section in the form of, for example, an oval profile for flow around, and the radial rays are made of hollow flattened pipes of containers forming aerodynamic trapezoidal surfaces, while the profiled ring with profiled pipes in combination form an aerodynamic scheme of the type ring plan. 12. The device according to claim 10 differs in that the entire annular internal area of the ring plane and the space between the radial pipes is tightened by a power lattice (mesh) surface, while the ring forms the power rim of such a tie, and the radial pipes are rigidly connected to the network. 13. The device according to claim 10 differs in that at the junctions of the radial pipes with the inner part of the ring, the ring is made thicker where spacious halls and auditoriums are located, 14. The device according to claim 11 is characterized in that the thickenings are equipped with large panoramic windows and portholes. 15. The device according to claim 10 differs in that drums with an elastic heat-resistant shell tailored in the form of an upper and lower dome are placed in the end parts of the central cylindrical module, which are laid spirally on the drum before the annular surface is launched into space and straightened before entering the atmosphere and landing , while the peripheral part (base) of the domes is attached circumferentially to the ring, with the upper dome being made more convex-concave than the lower one, and the internal space of the domes is inflated with gas, for example, when braking with an oncoming oncoming flow. 16. The device according to claim 13 is distinguished by the fact that the interdome space, inflated with gas, forms the aerodynamic shape of the descent spacecraft of the “headlight” type. 17. The device according to claim 11 is characterized in that the mesh (lattice) surface of the screed is used for radio engineering tasks, for example, as an auxiliary frame of an orbital reflector, while the annular rim is used to accommodate turns of an inductor of significant size, for example, made of superconducting materials. 18. A device for implementing the method according to claim 7, characterized in that the mesh surface of the screed before landing is used as a power network for deploying the membrane surface for braking, 19. A device for implementing the method according to claim 8, characterized in that the power circuit of the segment is made of a stacked structure, the frames of which are formed by a lattice surface and the stringers are a solid plane, the set is sheathed with outer shells with a large radius and inner shells with a smaller radius inserted into each other at a certain distance, the number of which can reach ten, the shells are equipped with windows, hatches and connecting fasteners, as well as sections of electrical and hydraulic lines, while transverse sealed bulkheads located perpendicular to the oncoming flow are made in the form of blinds.