RU2743061C1 - Rocket launch complex with a rocket-catapult vehicle for flights to the moon and back - Google Patents

Abstract

FIELD: transport space systems.SUBSTANCE: invention relates to transport space systems that launch from the Earth. The rocket launch complex includes rocket-catapult device (hereinafter - RCD) (4) and a two-stage rocket with cabin (3) for astronauts installed in it. The rocket is equipped with sustainer rocket engine (hereinafter - E) of first (18) and second (20) stages, as well as emergency E (24). On RCD (4) blocks of rocket carriers (9) with E (8), landing struts (12) with support footing (13) and brake E (30) are fixed, as well as parachute compartment (25) and amortizing cushion (34) with tank (33). RCD (4) is installed above the gas outlet pit of the launch facility. After separating the rocket from the spent RCD, the latter makes a descent on parachutes and lands on Earth with the help of struts (12), brake E (30) and cushion (34). The rocket continues its flight to the Moon, lands on its surface using support struts (21) of the second stage, takes off and returns to Earth.EFFECT: possibility of landing astronauts on the Moon and returning them to Earth.1 cl, 14 dwg

Description

The invention relates to space technology and can be used as a space vehicle for interplanetary flights from Earth to the Moon and back.

Known carrier rocket (LV) "Soyuz", containing a package of rocket blocks, in the form of a central block operating at the first and second stages, and four side blocks of the first stage, installed in the stabilization planes of the carrier rocket at an angle to the longitudinal axis of the central block of the second stages, as well as sequentially located block of the third stage, head fairing and payload, while the blocks of stages 1 and 2 include tanks of propellant components (oxidizer and fuel), two torus tanks on each block with components that ensure the operation of the propulsion system , cruise and steering liquid-propellant rocket engines (LRE) installed on each block, power units with ball bearings in the upper part of the first stage blocks, the upper power belt on the second stage block and power connections of the tail part of the package, and the lower part of the second stage block is cylindrical with a diameter smaller than the diameter of the upper power belt, the transitional part of the second block the steps from the upper power belt to the lower cylindrical part have a conical shape, while the upper power belt and the part of the second stage block located above it are made of a conical shape.

A spherical fuel tank and an oxidizer tank with spherical bottoms and a cylindrical tank shell aligned with the power body of the block are fixed on the cylindrical body of the third stage block. The radii of the spherical bottoms of the tanks are equal to half the diameter of the block body.

The power bearing shell of the unit along the length from the fuel tank to the docking surface of the unit with a transition compartment for attaching the head fairing and payload is supported by a longitudinal-transverse force set.

The instrumentation compartment, located in the upper part of the central unit and in the inter-tank compartment, contains instruments for control and measurement systems operating on the first and second flight stages of a space rocket (ILV).

On the block of the third stage, in the inter-tank compartment, there are control and measurement system instruments operating at the third stage of the flight of a space rocket.

The launch vehicle contains a device for ensuring the required temperature of the gaseous medium in the inter-tank and instrument compartments of the second and third stage units for instruments of control and measurement systems while the ILV is stationary in the launch device during its prelaunch preparation.

The device consists of a thermostatic air supply station located at the launch structure through the ground pipelines of the launch device, explosive pneumatic blocks of the launch vehicle and high-pressure transit pipelines fixed on the housings of the central block of the second stage, the block of the third stage, and dissipating the high-pressure air flow entering through the pipelines by heads (nozzles) fixed on the bodies inside the inter-tank and instrument compartments of the LV units.

As part of the known ILV, together with a three-stage launch vehicle of the "Soyuz" type, head fairings with discharged flaps and transition compartments with hull diameters equal to or slightly exceeding the diameter of the hull of the third stage of the launch vehicle are used.

The head fairings are equipped with drainage holes to equalize the air pressure inside and outside the head fairing during its operation as part of the ILV, and which do not allow protecting the payload from the effect of rapidly changing pressure gradients arising during ILV flight at maximum velocity heads.

The dumped flaps are interconnected by multi-link mechanical locks, the opening of which is carried out by rods from pyro-actuators triggered by a command from the LV control system.

The fairing flaps are attached to the transition compartment with mechanical locks, also triggered by a command from the launch vehicle control system.

The design of the joints of the wing fairing (HE) provides moisture protection of the payload, but, like the design of the drainage holes, does not provide the HE tightness when exposed to loads during the ILV flight.

Known carrier rocket (RU2149125), containing a package of two stages as part of the central block of the second and four side blocks of the first stage, installed in the stabilization planes of the carrier rocket at an angle to the longitudinal axis of the block of the second stage, as well as sequentially located third stage and payload , while the blocks of stages 1 and 2 include tanks of propellant components (oxidizer and fuel), two torus tanks on each side block, ensuring the operation of the propulsion system, propulsion and steering liquid-propellant rocket engines (LRE) installed on each block, power nodes with ball bearings in the upper part of the first stage blocks, the upper power belt on the second stage block and the power connections of the tail part of the package, and the lower part of the second stage block is made with a cylindrical diameter smaller than the diameter of the upper power belt, the transitional part of the second stage block from the upper power belt to the bottom has a conical shape, and the ratio of the volume of the fuel component tanks of the second stage block to the volume of the fuel component tanks of the first stage blocks is 0.895-0.989, while the upper power belt and the part of the second stage block located above it are cylindrical in shape with the ratio of their diameter to the diameter of the specified lower cylindrical part within 1.273 -1.371.

The closest analogue is a space rocket (RU2368542, publ .: 2009.09.27), containing a package of rocket blocks in the form of a central block of the first and second stages, four side blocks of the first stage, installed in the stabilization planes of the launch vehicle at an angle to the axis of the central block the second stage, as well as the sequentially located block of the third stage and the head fairing, while the blocks contain instruments for control systems, tanks of propellant components, sustainer and steering liquid-propellant rocket engines installed on each block, power units with ball bearings in the upper part of the blocks of the first stage, the upper power belt on the second stage block and the power rods of the tail part of the package, and the lower part of the second stage block is made with a cylindrical diameter smaller than the diameter of the upper power belt, and the transition part of the second stage block from the upper belt to the lower part has a conical shape, characterized in that cylindrical part of the head body about the fairing is made with the ratio of its diameter to the diameter of the casing of the third stage block in the range from 1.39 to 1.6 and the height to its diameter in the range from 1.2 to 1.65 and is connected by a conical transition compartment with the third stage block, when the height of the transitional compartment and the cylindrical shell of the third-stage fuel tank is made no more than 1.6 times the difference between the diameters of the head fairing and the fuel tank body, made in the form of the bearing cylindrical part of the structure of the third stage block with a lower spherical bottom with a diameter greater than the diameter of the third stage block, and on the load-bearing shell of the inter-tank compartment of the third stage, two annular frames are fixed, interconnected by two concentric plates, forming an annular collector, which, with its holes, ensures the distribution of thermostated air to the control system instruments; on the docking surfaces of the flaps of the head fairing and the transition compartment, sealing gaskets are fixed, and on the cylindrical part of the discharged flaps of the head fairing housing, drain valves for excessive internal pressure are fixed, while on the longitudinal-transverse power set and the bearing shell of the inter-tank compartment of the third stage block there are two stringers rigidly connected to each other by a cantilever platform for attaching the block of angular velocity sensors a control system designed for the formation by instruments of the control system of commands to control the movement of a space rocket on the steering liquid rocket engines at the first, second and third stages of flight of a space rocket, and on the bottom of the oxidizer tank in the inter-tank compartment of the second stage block on a platform adjusted relative to the stabilization planes block, taking into account the pressure in the tank, the second block of angular velocity sensors of the control system is fixed, intended for the formation by the control system devices of commands for controlling the movement of the space rocket with the elasticity of the structure of the space rocket body on the steering liquid propellant rocket engines of the central and side blocks of the first and second flight stages of the space rocket.

The disadvantages of the known technical solution, as well as the above-described devices, is that they do not allow the solution of the problem of landing astronauts on the Moon and returning them back to Earth.

So, the known rocket systems burn up to 80% of the rocket fuel, after which the stages of the launch vehicles are separated from the rocket and the remaining central stage is not able to fulfill the task of flying to the moon, as well as returning astronauts to Earth in a descent capsule. The solution of such a problem with known rocket systems will require the creation of a rocket of enormous mass and size.

The objective of the invention is to eliminate these disadvantages.

The technical result is the possibility of landing astronauts on the moon and returning them back to Earth.

The specified technical result is achieved due to the fact that a rocket-launch complex with a rocket-ejection apparatus for flights to the moon is declared, containing a launch pad with stocks, a rocket with a cockpit for cosmonauts and a rocket-catapult apparatus, where the rocket with a cockpit of cosmonauts is inside the rocket- catapult apparatus, and the rocket-ejection apparatus is located above the gas outlet pit, there are recesses on the gas outlet pit, on which power racks are installed on the support shoes; there are two rocket stages on the rocket, where the first rocket stage with rocket motors is located at the bottom of the rocket, on the second rocket stage with rocket engines there are hydraulic power support drains with support shoes for landing on the ground of the Earth or the Moon; power adapters are installed between the rocket stages to separate the stage with rocket engines after the propellant has run out; on top of the cockpit with the cosmonauts there are emergency solid-propellant rocket engines for sudden abandonment of the cockpit with the astronauts of the launch vehicle in an emergency; The rocket and catapult apparatus contains: a compartment for parachutes for landing on the ground of the Earth and a compartment where the electronic control units of the rocket and catapult apparatus are located in the launch mode, and at the bottom of the compartments on the body of the rocket and catapult apparatus there are movable mounts on which power support racks are installed with power rods attached to the body of the rocket and catapult apparatus; from below on the power support legs there are support shoes for landing on the ground of the Earth, and also on the power support legs there are braking solid-propellant rocket engines operating when landing on the ground, providing a soft landing on the ground; rocket launchers are installed on the rocket-ejection apparatus, inside of which rocket engines and taxiing rocket engines are installed; Between the launch vehicles at the bottom of the body of the rocket and catapult apparatus there is a compartment where are installed: a high-pressure cylinder with nitrogen and a rubber cushion to cushion the impact when landing on the Earth's ground.

Brief Description of Drawings

Figure 1 shows a general view of the rocket and the rocket-ejection apparatus.

Figure 2 shows a longitudinal section of the rocket-ejection apparatus.

Figure 3 shows a bottom view of the power part of the rocket-ejection apparatus.

Figure 4 shows a bottom view of the modified power part of the rocket-ejection apparatus.

Figure 5 shows a longitudinal section of the launch pad in the rocket launch preparation mode.

Figure 6 shows a cross-section of the launch pad in the rocket launch preparation mode.

Figure 7 shows a longitudinal section of the launch pad in the mode of launch and flight of the rocket.

Figure 8 shows an example of ejection of a rocket with astronauts from a rocket-ejection apparatus.

Figure 9 shows an example of the descent from a pre-space height with parachutes to the ground of the Earth of a rocket-catapult vehicle.

Figure 10 shows an example of a rocket-catapult vehicle landing on the Earth's ground.

Fig. 11 shows an example of a rocket with astronauts in the lunar landing mode.

Figure 12 shows a rocket with astronauts after landing on the lunar soil.

Figure 13 shows a rocket with astronauts in the mode of launch and flight from the ground of the Moon.

On Fig shows an example of the descent to the ground of the Earth with the parachute of the capsule of the cabin with the astronauts.

In the drawings: 1 - launch pad, 2 - slipways left and right, 3 - rocket cockpit, 4 - rocket-catapult apparatus, 5 - gas outlet pit, 6 - gas outlet ducts, 7 - direct-flow fans, 8 - nozzles of rocket-ejection rocket engines apparatus, 9 - launch vehicles of the rocket and catapult apparatus, 10 - AC motors, 11 - deepening in the gas outlet pit, 12 - power struts of the rocket and catapult apparatus, 13 - support shoes of the rocket and catapult apparatus, 14 - ladders with a flight of stairs, 15 - slipway elevator cabin, 16 - slipway electrical machine hall, 17 - first stage of the rocket, 18 - rocket engines of the first stage, 19 - second stage of the rocket, 20 - rocket engines of the second stage, 21 - hydraulic power support legs, 22 - support shoes for the second rocket stages, 23 - power adapters of the rocket stages, 24 - emergency solid-propellant engines of the rocket cockpit, 25 - parachute compartment of the rocket and catapult apparatus, 26 - the earth's surface (surface of the Earth), 27 - compartment with electronic units of the rocket and catapult apparatus, 28 - movable mounts on which the power support legs of the rocket and ejection apparatus are installed, 29 - power rods on the power support legs, 30 - braking solid-propellant rocket engines, 31 - taxiing rocket engines, 32 - compartment at the bottom of the rocket and catapult apparatus, 33 - high pressure cylinder inside the compartment of the rocket and catapult apparatus, 34 - rubber cushion, 35 - rocket cockpit capsule, 36 - pilot parachute of the rocket and catapult apparatus, 37 - main the parachute of the rocket-ejection apparatus, 38 - the cover at the bottom of the body of the rocket-ejection apparatus, 39 - the surface of the Moon, 40 - the pilot parachute of the rocket cockpit, 41 - the main parachute of the rocket cockpit.

Implementation of the invention

The rocket launch complex with the rocket-ejection apparatus contains: a launch pad 1, on which the slipways 2 are located left and right, between them a rocket with a cabin 3 for cosmonauts and a rocket-ejection apparatus 4 is installed.

A rocket with a cabin of 3 cosmonauts is inside the rocket-ejection apparatus 4.

The rocket and catapult device 4 is located above the gas outlet 5, inside which there are gas outlet ducts 6, in which there are direct-flow fans 7, ejecting gas from the nozzles 8 of the rocket engines of the launch vehicles 9 to the left and right of the rocket and catapult device 4.

At the time of the launch of the rocket-catapult apparatus 4 direct-flow fans 7, powered by 10 alternating current electric motors for the time of the launch of the rocket-catapult apparatus 4, inside which a rocket with a cabin 3 and astronauts is installed.

On the gas outlet 5 there are recesses 11, on which the power struts 12 are installed on the support shoes 13. After installing the support shoes 13 into the recess 11, the support shoes 13 are fixed with hydraulic locking locks (not shown in the drawings).

On the launch pad 1 there are movable left and right slipways 2 on a wheeled electrical installation for moving slipways 2 along the railway track, inside slipways 2 there are 14 staircases with a flight of stairs, and there is also an elevator 15 with elevator cabins and an electric machine hall of the elevator 16 for landing astronauts in the cabin 3 rockets.

There are two rocket stages on the rocket, where the first rocket stage 17 with rocket motors 18 is located at the bottom of the rocket. On the second rocket stage 19 with rocket engines 20, hydraulic power support drains 21 with support shoes 22 are installed for landing on the ground of the Earth or the Moon.

Power adapters 23 are installed between the rocket stages 19 to separate the stage 19 with the rocket engines 18 after the propellant has run out. On top of the cabin 3 with the astronauts there are emergency solid-propellant rocket engines 24 for a sudden exit from the cabin with the launch vehicle astronauts in an emergency.

The rocket-ejection apparatus 4 contains: a compartment 25 for parachutes for landing on the ground of the Earth 26 (Fig. 9 and Fig. 10) and a compartment 27, where the electronic control units of the rocket-catapult apparatus 4 are located in the launch mode, and from the bottom of the compartments on the body of the rocket -catapult apparatus 4 there are movable mounts 28, on which power support legs 12 with power rods 29 are installed, attached to the body of the rocket-catapult apparatus 4. From below, on the power support posts 12, support shoes 13 are installed for landing on the ground of the Earth 26, as well as on power support struts 12 are braking solid-propellant rocket motors 30 operating when landing on the ground of the Earth 26, providing a soft landing on the ground of the Earth 26 (Fig. 9 and Fig. 10).

On the rocket and catapult apparatus 4, launch vehicles 9 are installed, inside which rocket engines 8 are installed, for example, RD-180 with a nozzle diameter of 1800 mm, as well as taxiing rocket engines 31, for example, RD-22 (Fig. 3).

Any necessary changes in the power rocket system and the use of other rocket engines, for example, RD-120 (Fig. 4), are possible.

Between the carrier rockets at the bottom of the body of the rocket-ejection apparatus 4 there is a compartment 32 (Fig. 2), where are installed: a high-pressure cylinder 33 with nitrogen and a rubber cushion 34 to mitigate the impact when landing on the ground of the Earth (Fig. 10) of rocket engines 8.

The principle of operation of the rocket-launch complex with the rocket-ejection apparatus is as follows.

From the assembly shop on the railway platform, a rocket with a rocket-catapult apparatus 4 is brought to the gas outlet 5 and it is installed with power support posts 12, on which support shoes 13 are installed in the recesses 11 located near the edge of the pit 5. After that, in the recesses 11 fixing the support shoes 13 with hydraulic locks (not shown in the drawings) for a stable position in preparation for the launch of the rocket and the rocket-catapult apparatus 4. To the vertically installed rocket on the launch pad 1 along the railway track, the slipways 2 are brought closer to the left and right using an electric drive ( not shown in the drawings). On the slipways 2 there is everything necessary for the preparation and landing of the astronauts in the rocket cabin 3 of the staircase 14 with a flight of stairs, as well as the elevator, where the astronauts along the elevator shaft go up to the rocket cabin 3 using the electric machine hall of the elevator 16 along the elevator car 15.

After the astronauts have landed in the capsule 35 of the rocket cabin 3 and the preparation of the rocket for launch is completed, the slipway 2 is moved away from the rocket. Direct-flow fans 7 are turned on, rotated by electric motors 10. With the help of these fans 7, the exhaust gases from the rocket and the rocket-ejection apparatus 4 are accelerated after the start of the rocket engines 8. The support shoes 13 are uncoupled using hydraulic locks (not shown in the drawings), the rocket engines 8 are started ...

After the separation of the rocket and the rocket-ejection apparatus 4 from the surface of the launch pad 1 (Fig. 7) upwards and its departure to the pre-space height.

In the event of an emergency, the rocket 3 with the cosmonauts is ejected from the rocket-catapult apparatus 4 (Fig. 8), and the first stage 17 of the rocket with rocket engines 18 operates on the rocket.

On the rocket-ejection apparatus 4, the power plant of the launch vehicles 9 with rocket engines 8 stops working and the rocket-ejection apparatus 4 descends down to the earth's surface 26. From the compartments 25, the main parachutes 37 (Fig. 9) and the rocket-catapult apparatus 4 approaches the earth's surface.

At the right time, the height above the earth's surface includes braking solid-propellant engines 30 for braking and hovering the rocket and catapult apparatus 4, the electronic unit system of which sends a signal to the compartment 32, where the cylinder 33 with a high nitrogen pressure is located and this gas from the cylinder 33 is filled with a rubber cushion 34 , the cover 38 of the compartment 32 is folded back, a rubber cushion 34 is revealed, which softens the impact during landing on the Earth 26 of the rocket stages 9, where the rocket motors 8 with nozzles are installed (Fig. 10).

With the help of the first stage 17 of the rocket, the rocket with the astronauts reaches the surface of the soil 39 of the Moon (Fig. 11).

There is a separation of the first stage 17 of the rocket, after which, having in the second stage 19, hydraulic power support legs 21 with support shoes 22 are moved apart from the body of the second stage 19 of the rocket, the rocket with the astronauts lands on the ground 39 of the Moon (Fig. 12) after stay astronauts on the moon, astronauts are in the capsule 35 of the cockpit 3 rocket. The rocket takes off using the second stage 19 with rocket engines 20 (Fig. 13).

The flight of the rocket is directed towards the Earth. When the rocket approaches the Earth, the second stage 19 with rocket engines 20 is separated, and the skin is separated from the cabin 3.

The capsule 35 makes its descent to Earth 26, where the main parachute 41 is opened using the pilot parachute 40.

The capsule 35 makes a soft landing with the astronauts (Fig. 14) on the surface of the Earth (26).

Claims (1)

A rocket launch complex with a rocket-ejection apparatus for flights to the moon, containing a launch pad with slipways, a rocket with a cockpit for astronauts and a rocket-ejection apparatus, and the rocket with a cockpit for astronauts is located inside the rocket-ejection apparatus, and the rocket-ejection apparatus is located above the gas outlet, while on the gas outlet there are depressions on which power racks are installed on the support shoes, the rocket has two rocket stages, and the first rocket stage with rocket engines is located at the bottom of the rocket, on the second rocket stage with rocket engines, hydraulic power support legs are installed with support shoes for landing on the ground of the Earth or the Moon, power adapters are installed between the rocket stages to separate the stage with rocket engines after the rocket fuel has run out, emergency solid-propellant rocket engines are located on top of the cabin with the astronauts for emergency leaving the cabin with the astronauts in a emergency situation of launch vehicles, while the rocket-ejection apparatus contains a compartment for parachutes for landing on the ground of the Earth and a compartment where the electronic control units of the rocket-ejection apparatus are located in the launch mode, and from the bottom of the compartments on the body of the rocket-ejection apparatus there are movable mounts on which power support legs are installed with power rods attached to the body of the rocket-catapult apparatus, while support shoes are installed on the power support legs from below for landing on the Earth's ground, braking solid-propellant rocket engines are also located on the power support legs, operating when landing on the Earth's ground, providing a soft landing on the ground of the Earth, rocket launchers are installed on the rocket-ejection apparatus, inside which rocket engines and steering rocket engines are installed, and between the carrier rocket at the bottom of the rocket-ejection apparatus there is a compartment where a high-pressure cylinder with nitrogen and rubber is installed New impact cushion when landing on the ground.

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