A cold air reverse thrust and air cushion landing device for manned spacecraft

Abstract

The present invention relates to the field of spacecraft return landing technology, and in particular to a cold air reverse thrust and air cushion landing device for a manned spacecraft, comprising a return capsule, a parachute installed in the top of the return capsule, a jet assembly installed in the bottom of the return capsule, a metal bottom fixedly connected to the bottom of the return capsule, a cavity formed between the inner wall of the metal bottom and the bottom surface of the return capsule; the jet assembly comprises an air supply portion arranged in the bottom of the return capsule, the air supply portion is connected to a plurality of nozzles, and the nozzles are arranged in the cavity. The present invention ejects the gas in the air supply portion through the nozzle, so that the gas ejected by the nozzle can not only generate reverse thrust, but also form a supporting force in the cavity to perform air cushion cushioning on the return capsule when the metal bottom is close to the ground, which can effectively consume the impulse of the return capsule, so that the return capsule can be buffered and land smoothly.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft return landing, in particular to a cold air reverse thrust and air cushion buffer landing device for a manned spacecraft. Background Art

[0002] The landing of a manned spacecraft is very critical, which is related to the safety of the crew and the safety of the spacecraft equipment. When the spacecraft is recovered, the parachute is first opened at high altitude to slow down. The vertical descent speed after the parachute is fully opened is 6-10m / s, and the horizontal speed is related to the local wind speed. If it touches the ground at this vertical speed, the impact is still very large, and the safety of the crew cannot be guaranteed. It is very likely to cause fractures or falls in certain parts of the body. Therefore, cushioning and shock reduction measures are indispensable, and the descent speed before touching the ground needs to be controlled to no more than 1m / s. At present, the following methods are usually used for landing cushioning: 1. Fixed-engine reverse thrust, which has the advantages of small size, light weight, high reliability, and the disadvantage is the existence of pyrotechnics. Management and transportation problems, the outsole needs to be thrown away before opening the parachute; 2. Cushion airbag type, its advantage is that there is no problem of managing pyrotechnics, it is inflated in advance in the air, can be used for landing on water or land, the cushioning effect is ideal, the disadvantage is that the structure is complicated, the heat-resistant outsole needs to be thrown away in advance, the center of gravity of the return capsule is high during landing, and it is easy to overturn; 3. Sea splashdown type, its advantage is that it uses seawater for cushioning, no other cushioning landing equipment is required, and the cushioning effect is good. The disadvantage is that the return capsule is required to be waterproof and needs to be salvaged from the sea; therefore, there is an urgent need for a cold air reverse thrust and air cushion cushioning landing device for manned spacecraft, which can not only effectively avoid the shortcomings of the above-mentioned solutions, but also effectively ensure the advantages of strong operability, convenience, durability and low cost. Summary of the invention

[0003] The purpose of the present invention is to provide a cold air reverse thrust and air cushion landing device for a manned spacecraft to solve the problems existing in the above-mentioned prior art.

[0004] To achieve the above-mentioned object, the present invention provides the following scheme: a cold air reverse thrust and air cushion landing device for a manned spacecraft, comprising a return capsule, a parachute is installed in the top of the return capsule, a jet assembly is installed in the bottom of the return capsule, a metal bottom is fixedly connected to the bottom of the return capsule, and a cavity is formed between the inner wall of the metal bottom and the bottom surface of the return capsule;

[0005] The jet assembly includes an air supply portion arranged in the bottom of the return capsule, the air supply portion is connected to a plurality of nozzles, and the nozzles are arranged in the cavity.

[0006] Preferably, the return capsule is conical in shape, and the diameter of the bottom surface of the return capsule is larger than the diameter of the top surface of the return capsule.

[0007] Preferably, the metal outsole is in a circular ring shape.

[0008] Preferably, a plurality of the nozzles are arranged close to the inner wall of the metal bottom.

[0009] Preferably, a plurality of the nozzles are arranged at equal intervals.

[0010] Preferably, the gas supply part includes a plurality of high-pressure gas cylinders, both ends of the high-pressure gas cylinders are respectively connected with four-way pipe fittings, a first connecting pipe is connected between the opposite ends of two adjacent four-way pipe fittings, and the other two ends of the four-way pipe fittings are respectively connected with second connecting pipes, and the second connecting pipes are connected to the nozzle.

[0011] Preferably, any one of the first connecting pipes is connected to a charging valve.

[0012] Preferably, a solenoid valve is installed on the second connecting pipe.

[0013] Preferably, all the solenoid valves and the inflation valves are electrically connected to the controller of the return capsule.

[0014] Preferably, the nozzle is in the shape of a bell mouth, and the diameter of the air outlet end of the nozzle is larger than the diameter of the air inlet end of the nozzle.

[0015] The present invention discloses the following technical effects:

[0016] The present invention ejects the gas in the air supply part through the nozzle, so that the gas ejected from the nozzle can not only generate reverse thrust, but also form a supporting force in the cavity when the metal bottom is close to the ground to perform an air cushion effect on the return capsule, which can effectively consume the impulse of the return capsule and enable the return capsule to be cushioned and land smoothly.

[0017] The present invention has a simple structure and is easy to configure, and can greatly reduce the cost of use; it is suitable for onshore recovery and can be reused, and the maintenance cost of reuse after recovery is low, and it can be reused by only refilling the high-pressure gas cylinder with high-pressure gas. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 It is a front cross-sectional structural schematic diagram of the present invention;

[0020] Figure 2 This is a schematic diagram of the structure of the jet assembly of the present invention installed in the return capsule;

[0021] Figure 3 It is a schematic diagram of the structure of the jet assembly of the present invention;

[0022] Figure 4 This is a schematic diagram of the cold air reverse thrust and air cushion landing device of the present invention;

[0023] Figure 5 It is the total impulse curve of the nozzle and the cavity acting together in the present invention;

[0024] Figure 6 This is the cavity pressure curve of the present invention (gas supply starts at -0.5s);

[0025] Figure 7 is the total thrust curve of the nozzle of the present invention (air supply starts at -0.5s);

[0026] Among them, 1. Return capsule; 2. Metal bottom; 3. Cavity; 4. High-pressure gas cylinder; 5. First connecting pipe; 6. Inflation valve; 7. Second connecting pipe; 8. Solenoid valve; 9. Nozzle; 10. Four-way pipe fitting; 11. Ground; 12. Support force; 13. Nozzle thrust; 14. Jet airflow. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] Embodiment 1

[0030] Reference Figure 1-Figure 4 The present invention provides a cold air reverse thrust and air cushion landing device for a manned spacecraft, comprising a return capsule 1, a parachute is installed in the top of the return capsule 1, a jet assembly is installed in the bottom of the return capsule 1, a metal bottom 2 is fixedly connected to the bottom of the return capsule 1, and a cavity 3 is formed between the inner wall of the metal bottom 2 and the bottom surface of the return capsule 1; the jet assembly includes an air supply part arranged in the bottom of the return capsule 1, the air supply part is connected to a plurality of nozzles 9, and the nozzles 9 are arranged in the cavity 3.

[0031] The present invention ejects the gas in the air supply part through the nozzle 9, so that the gas ejected from the nozzle 9 can not only generate reverse thrust, but also form a supporting force 12 in the cavity 3 to perform an air cushion effect on the return capsule 1 when the metal bottom 2 is close to the ground, which can effectively consume the impulse of the return capsule 1 and enable the return capsule 1 to be cushioned and land smoothly.

[0032] The present invention has a simple structure and is easy to configure, and can greatly reduce the cost of use; it is suitable for onshore recovery and can be reused, and the maintenance cost of reuse after recovery is low, and it can be reused by only refilling the high-pressure gas cylinder 4 with high-pressure gas.

[0033] According to a further optimization scheme, the return capsule 1 is conical in shape, and the diameter of the bottom surface of the return capsule 1 is larger than the diameter of the top surface of the return capsule 1.

[0034] According to a further optimized solution, the metal outsole 2 is in a circular ring shape.

[0035] In a further optimized solution, several nozzles 9 are arranged close to the inner wall of the metal base 2. By placing the nozzles 9 close to the inner wall of the metal base 2, not only the range of the reverse thrust is effectively increased, but also when the metal base 2 is close to the ground 11, a part of the jet airflow 14 ejected from the nozzle 9 flows along the bottom of the metal base 2 to the outside of the cavity 3, and the other part of the jet airflow 14 can form a supporting force 12 in the cavity 3 after contacting the ground. At the same time, after the nozzle 9 ejects the jet airflow 14, it also consolidates the nozzle thrust 13, so that an air cushion is formed in the cavity 3, which can effectively consume the remaining momentum of the return capsule and make the return capsule 1 land smoothly, thereby ensuring the safety of the occupants in the return capsule 1.

[0036] To further optimize the solution, a plurality of nozzles 9 are arranged at equal intervals.

[0037] According to a further optimization scheme, the gas supply part includes a plurality of high-pressure gas cylinders 4, both ends of which are respectively connected to a four-way pipe fitting 10, a first connecting pipe 5 is connected between opposite ends of two adjacent four-way pipe fittings 10, and the other two ends of the four-way pipe fittings 10 are respectively connected to a second connecting pipe 7, and the second connecting pipe 7 is connected to a nozzle 9.

[0038] According to a further optimized solution, any one of the first connecting pipes 5 is connected to a charging valve 6 .

[0039] In order to avoid the management and transportation problems of pyrotechnics and improve the safety of the entire process of spacecraft from assembly, transportation, testing, launch to recovery, the high-pressure gas cylinder 4 is filled with high-pressure nitrogen, and the high-pressure gas cylinder 4 is filled with nitrogen through the filling valve 6.

[0040] To further optimize the solution, a solenoid valve 8 is installed on the second connecting pipe 7 .

[0041] To further optimize the solution, all the solenoid valves 8 and the inflation valve 6 are electrically connected to the controller of the return capsule 1 .

[0042] In a further optimized solution, the nozzle 9 is bell-mouthed, and the diameter of the air outlet end of the nozzle 9 is larger than the diameter of the air inlet end of the nozzle 9. By making the nozzle 9 bell-mouthed, the reverse thrust is effectively improved.

[0043] Working process: before the spacecraft is launched, the high-pressure gas cylinder 4 is filled with nitrogen through the inflation valve 6; when the spacecraft completes the space mission, during the process of the return capsule 1 returning to the ground, when the return capsule 1 enters the atmosphere, the parachute on the top of the return capsule 1 is opened, and the vertical landing speed of the return capsule 1 is 6-10m / s through the parachute; the controller of the return capsule 1 is electrically connected to the altimeter, and the height from the ground is continuously measured by the altimeter. At the required air supply height, the solenoid valve 8 can be instantly opened to supply air to the cavity 3. When the distance between the return capsule 1 and the ground 11 is 5 meters, the controller of the return capsule 1 can open several solenoid valves 8 at the same time 0.5 seconds in advance, and the high-pressure nitrogen in the high-pressure gas cylinder 4 is quickly released through the nozzle 9, which generates a large upward thrust on the return capsule 1, decelerating the return capsule 1, and the jet airflow 14 ejected from the nozzle 9 can build up a certain pressure in the cavity 3 for the outflowing high-pressure nitrogen at the moment of touching the ground, which can consume the remaining momentum of the return capsule 1 and make the return capsule 1 land smoothly, thereby ensuring the safety of the occupants in the return capsule 1.

[0044] Embodiment 2

[0045] Reference Figure 1-Figure 7 There are two high-pressure gas cylinders 4, eight nozzles 9, and the metal base 2 is made of closed-cell foam aluminum material. The specific parameters are shown in Table 1:

[0046] Table 1

[0047]

[0048] The high-pressure gas cylinder 4 is a T800 high-strength carbon fiber wrapped gas cylinder. The volume of each high-pressure gas cylinder 4 is 50L, the volume of two high-pressure gas cylinders 4 is 100L in total, the maximum working pressure is 35MPa, the filling fatigue life is 100 times, and the interface is aerospace standard DN32 37° conical external thread after conversion. Each high-pressure gas cylinder 4 has two interfaces, and the high-pressure gas cylinder 4 is used to store high-pressure nitrogen.

[0049] The maximum working pressure of the solenoid valve 8 is 35MPa, the diameter is 32mm, the power supply is 24V, it is normally closed, and there are 8 of them. When the controller of the return capsule 1 determines that it is 5 meters above the ground, it sends a command 0.5 seconds in advance to open the 8 solenoid valves 8 and supply air to the 8 nozzles 9 at the same time.

[0050] The high-pressure gas cylinder 4 is filled with 35MPa nitrogen through the charging valve 6, and a pressure sensor is installed on the charging valve 6. The pressure sensor is used to detect the pressure in the high-pressure gas cylinder 4. The diameter of the connection between the charging valve 6 and the first connecting pipe 5 is 4mm.

[0051] The nozzle 9 is a key component of the entire device. The airflow first flows through the convergent section of the nozzle 9, reaches the speed of sound when reaching the throat, and then flows through the expansion section to accelerate to supersonic speed, which can generate a large thrust. The reverse thrust force generated when the high-pressure nitrogen flows through the eight nozzles 9 can meet the landing cushioning requirements.

[0052] The first connecting pipe 5 and the second connecting pipe 7 are both stainless steel seamless pipes with an outer diameter of 40 mm and an inner diameter of 32 mm, which can withstand a pressure of 35 MPa. According to aerospace standards, the first connecting pipe 5 and the second connecting pipe 7 are welded to the spherical joint and installed on the high-pressure gas cylinder 4, the solenoid valve 8, the nozzle 9 and other components through the outer sleeve nut. The welded first connecting pipe 5 and the second connecting pipe 7 need to be verified by a 52.5 MPa water pressure test before formal installation.

[0053] Before the spacecraft is launched, the high-pressure gas cylinder 4 is filled with nitrogen to 35MPa through the inflation valve 6; when the return capsule 1 needs to return to the ground, the return capsule 1 opens the parachute on the top of the return capsule 1 after entering the atmosphere, and the vertical landing speed is 6-10m / s through the parachute; when the return capsule 1 is 5 meters above the ground, the controller of the return capsule 1 will open 8 solenoid valves 8 at the same time 0.5 seconds in advance, and the high-pressure nitrogen in the high-pressure gas cylinder 4 is quickly released through the nozzle 9, which generates a large upward thrust on the return capsule 1, decelerating the return capsule 1. The high-pressure nitrogen flowing out at the moment of touching the ground can build up a certain pressure in the cavity 3, which can eliminate the impulse range required for the return capsule 1 to cushion the landing within 0.2s after the return capsule 1 touches the ground, so that the return capsule 1 lands smoothly, thereby ensuring the safety of the occupants in the return capsule 1.

[0054] In the description of the present invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0055] The embodiments described above are only descriptions of the preferred modes of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A cold air reverse thrust and air cushion landing device for a manned spacecraft, characterized in that: The invention comprises a return capsule (1), wherein a parachute is installed in the top of the return capsule (1), a jet assembly is installed in the bottom of the return capsule (1), a metal base (2) is fixedly connected to the bottom of the return capsule (1), and a cavity (3) is formed between the inner wall of the metal base (2) and the bottom surface of the return capsule (1); The jet assembly comprises an air supply portion arranged in the bottom of the return capsule (1), the air supply portion being connected to a plurality of nozzles (9), and the nozzles (9) being arranged in the cavity (3); The metal base (2) is in the shape of a ring, and a plurality of the nozzles (9) are arranged close to the inner wall of the metal base (2), and the plurality of the nozzles (9) are arranged at equal intervals; The gas supply unit comprises a plurality of high-pressure gas cylinders (4), both ends of the high-pressure gas cylinders (4) are respectively connected to a four-way pipe fitting (10), a first connecting pipe (5) is connected between opposite ends of two adjacent four-way pipe fittings (10), and the other two ends of the four-way pipe fittings (10) are respectively connected to a second connecting pipe (7), and the second connecting pipe (7) is connected to the nozzle (9).

2. The cold air reverse thrust and air cushion landing device for a manned spacecraft according to claim 1, characterized in that: The return capsule (1) is conical in shape, and the diameter of the bottom surface of the return capsule (1) is greater than the diameter of the top surface of the return capsule (1).

3. The cold air reverse thrust and air cushion landing device for a manned spacecraft according to claim 1, characterized in that: Any one of the first connecting pipes (5) is connected to a charging valve (6).

4. The cold air reverse thrust and air cushion landing device for a manned spacecraft according to claim 3, characterized in that: A solenoid valve (8) is installed on the second connecting pipe (7).

5. The cold air reverse thrust and air cushion landing device for a manned spacecraft according to claim 4, characterized in that: All the solenoid valves (8), the inflation valves (6) and the controller of the return capsule (1) are electrically connected.

6. The cold air reverse thrust and air cushion landing device for a manned spacecraft according to claim 1, characterized in that: The nozzle (9) is in the form of a bell mouth, and the diameter of the air outlet end of the nozzle (9) is larger than the diameter of the air inlet end of the nozzle (9).

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