Reusable propulsion system for manned spacecraft

Abstract

The present application provides a kind of manned spacecraft reusable propulsion system related to space propulsion system technical field, including gas cylinder module, storage tank module, gas circuit valve module, blowing module, discharge module and engine module, gas cylinder module downstream is connected gas circuit valve module, gas circuit valve module is connected storage tank module and blowing module respectively, storage tank module downstream is connected discharge module, blowing module, storage tank module and discharge module are connected engine module respectively;Spacecraft before return, gas cylinder module is pressurized to storage tank module by gas circuit valve module;Spacecraft before landing ground, the discharge of propellant is realized by discharge module, blowing module is blown to engine module;Spacecraft after landing, storage tank module is cleaned, dried, blown, gas circuit valve module carries out pressure reducing valve performance test, engine module carries out inspection, maintenance, realizes system reuse.The present application uses green non-toxic propellant, safety is good, has reusable capacity, has universal applicability.

Description

Technical Field

[0001] The present invention relates to the technical field of space propulsion systems, and in particular to a reusable propulsion system for a manned spacecraft. Background Art

[0002] Once the technology to escape near-Earth space became available, humans began manned space exploration. Beginning in the 1960s, the Soviet Union, the United States, and China successively achieved manned space flight. China completed the first flight test of the Shenzhou-1 manned spacecraft in 1999, and by 2022, the construction of the Chinese Space Station had been completed, enabling astronauts to reside in orbit and conduct various space science experiments.

[0003] With the development of space exploration, space exploration technology has made tremendous progress. To reduce development costs, major space powers and aerospace companies have begun developing reusable space technology. Space-X pioneered the reuse of its first-stage rocket engine, further promoting the development of reusable space technology. Space technology is a high-risk and high-cost industry. If reuse can be achieved, it will greatly reduce R&D costs and time, with significant economic and social benefits. Summary of the Invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a reusable propulsion system for a manned spacecraft.

[0005] According to the present invention, a reusable propulsion system for a manned spacecraft includes a gas cylinder module, a tank module, a gas circuit test module, a purge module, an exhaust module, and an engine module. The gas cylinder module is connected downstream to a gas circuit valve module, which is respectively connected to the tank module and the purge module. The tank module is connected downstream to an exhaust module, and the purge module, tank module, and exhaust module are respectively connected to the engine module.

[0006] Before the spacecraft returns, the gas cylinder module pressurizes the tank module through the gas path valve module; before the spacecraft lands, the propellant is discharged through the discharge module, and the engine module is blown away by the blowdown module; after the spacecraft lands, the tank module is cleaned, dried, and blown away, the gas path valve module performs a pressure reducing valve performance test, and the engine module is inspected and maintained to achieve system reuse.

[0007] Preferably, the engine module uses green and non-toxic HAN-based propellant.

[0008] Preferably, the gas cylinder module includes a gas cylinder, a gas charging valve and a pressure sensor, and the gas cylinder is fixed upstream of the gas charging valve and the pressure sensor.

[0009] Preferably, the gas circuit valve module comprises a gas circuit high pressure electric explosion valve, a gas circuit high pressure self-locking valve, a high pressure test port, a pressure reducing valve, a low pressure test port and a gas circuit low pressure self-locking valve, the gas circuit high pressure electric explosion valve and the gas circuit high pressure self-locking valve are connected in sequence between the inflation valve and the high pressure test port, the high pressure test port is connected downstream with the pressure reducing valve, the pressure reducing valve is connected downstream with the low pressure test port and the gas circuit low pressure self-locking valve, and the gas circuit low pressure self-locking valve is connected downstream with the gas circuit transverse self-locking valve, the pressure sensor, the tank module and the blowing module respectively.

[0010] Preferably, the gas circuit high pressure self-locking valve and the gas circuit low pressure self-locking valve are closed, the high pressure test port is connected with high pressure nitrogen gas of a specified flow and pressure, and the low pressure test port is connected with the reduced pressure nitrogen gas, so as to test the outlet pressure of the pressure reducing valve.

[0011] Preferably, the tank module comprises a safety valve, a tank gas end adding and discharging valve, a tank, a tank liquid end adding and discharging valve, a propellant concentration test port, a tank management self-locking valve and a liquid circuit test port, the upstream of the safety valve is connected with the gas circuit low pressure self-locking valve, the downstream of the safety valve is connected with the tank gas end adding and discharging valve and the inlet of the tank, the downstream of the tank is connected with the tank liquid end adding and discharging valve, the tank management self-locking valve and the pressure sensor, the tank is integrated with the propellant concentration test port, the upstream of the tank management self-locking valve is connected with the tank outlet, and the downstream of the tank management self-locking valve is connected with the liquid circuit test port, the discharge module and the engine module.

[0012] Preferably, the discharge module comprises a propellant discharge self-locking valve, a propellant discharge check valve and a filter, the downstream of the tank management self-locking valve is connected with the inlet of the propellant discharge self-locking valve, the downstream of the propellant discharge self-locking valve is connected with the propellant discharge check valve, and the outlet of the propellant discharge check valve is provided with the filter.

[0013] Preferably, the blowing module comprises a blowing electric explosion valve and a blowing check valve, the upstream of the blowing electric explosion valve is connected with the gas circuit low pressure self-locking valve, the downstream of the blowing electric explosion valve is connected with the blowing check valve, the downstream of the blowing check valve is connected with the inlet of the engine management self-locking valve in the engine module and the outlet of the tank management self-locking valve, and the downstream of the engine management self-locking valve is connected with the attitude control engine in the engine module.

[0014] Preferably, the attitude control engine nozzle adopts a single-sided adhesive polyimide film, the diameter of the polyimide film is larger than that of the engine nozzle by mm, and the polyimide film is adhered to the outer wall of the engine nozzle through a circumferential outside circle and a 12mm*8mm square handle.

[0015] Preferably, the pressure sensor is fixed between the gas cylinder and the inflation valve, the gas circuit low pressure self-locking valve and the gas circuit transverse self-locking valve, the tank liquid end adding and discharging valve and the tank management self-locking valve respectively.

[0016] Compared with the prior art, the present application has the following beneficial effects:

[0017] (1) The present application uses HAN-based propellant as the energy working medium of the propulsion system, realizes the non-toxicity of the spacecraft propellant medium, ensures the safety of astronauts, and improves the safety of spacecraft maintenance, testing, and refueling processes.

[0018] (2) The present application can discharge all the remaining propellant before the spacecraft lands on the ground, and blow off the residual propellant in the engine and liquid pipeline, which improves the safety of the spacecraft landing process and provides favorable conditions for the inspection and testing of the subsequent reuse process of the spacecraft.

[0019] (3) The present application carries out reuse design from component products to system integration, formulates reuse guidelines for products at all levels, and has reuse capability for components and propulsion systems, which reduces development costs and saves development time. BRIEF DESCRIPTION OF DRAWINGS

[0020] Other features, objects, and advantages of the present application will become more apparent through reading the detailed description of the non-limiting embodiments with reference to the following drawings:

[0021] Figure 1 is a schematic diagram of a reusable propulsion system for manned spacecraft;

[0022] Figure 2 is a schematic diagram of a reusable tank;

[0023] Figure 3 is a schematic diagram of online testing of a pressure reducing valve;

[0024] Figure 4 is a schematic diagram of protection of the open part of propellant discharge;

[0025] Figure 5 is a schematic diagram of protection of the open part of the engine nozzle.

[0026] Reference numerals in the drawings:

[0027] 1-gas cylinder, 2-charging valve, 3-pressure sensor, 4-high pressure gas path electric explosion valve, 5-gas path high pressure self-locking valve, 6-high pressure test port, 7-pressure reducing valve, 8-low pressure test port, 9-gas path low pressure self-locking valve, 10-gas path transverse self-locking valve, 11-safety valve, 12-blowing electric explosion valve, 13-blowing check valve, 14-engine management self-locking valve, 15-tank gas end filling and draining valve, 16-tank, 17-tank liquid end filling and draining valve, 18-propellant concentration test port, 19-tank management self-locking valve, 20-propellant discharge self-locking valve, 21-propellant discharge check valve, 22-filter, 23-attitude control engine, 24-liquid path test port. DETAILED DESCRIPTION

[0028] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0029] Example 1

[0030] According to the present invention, a reusable propulsion system for a manned spacecraft is provided. Figure 1 As shown, it includes a gas cylinder module, a tank module, a gas circuit test module, a purge module, an exhaust module and an engine module. The gas cylinder module is connected downstream to a gas circuit valve module, which is respectively connected to the tank module and the purge module. The tank module is connected downstream to an exhaust module, which is respectively connected to the engine module.

[0031] Before the spacecraft returns, the gas cylinder module pressurizes the tank module through the gas path valve module; before the spacecraft lands, the propellant is discharged through the discharge module, and the engine module is blown away by the blowdown module; after the spacecraft lands, the tank module is cleaned, dried, and blown away, the gas path valve module performs a pressure reducing valve performance test, and the engine module is inspected and maintained to achieve system reuse.

[0032] The propulsion system uses green, non-toxic HAN-based propellants, which are non-toxic, low-temperature, high-energy, and highly safe. The complete decomposition products of HAN-based propellants are N2, H20, and CO2. The theoretical decomposition and combustion temperature reaches over 1200°C, higher than the 9000°C to 1000°C range of conventional single-component hydrazine materials, resulting in higher energy.

[0033] Example 2

[0034] This embodiment 2 is completed on the basis of embodiment 1. Figure 1 As shown, specifically:

[0035] The gas cylinder module includes a gas cylinder 1, an inflation valve 2 and a pressure sensor 3; the gas circuit valve module includes a high-pressure gas circuit electric explosion valve 4, a gas circuit high-pressure self-locking valve 5, a high-pressure test port 6, a pressure reducing valve 7, a low-pressure test port 8 and a gas circuit low-pressure self-locking valve 9; the tank module includes a safety valve 11, a tank gas end adding and discharging valve 15, a tank 16, a tank liquid end adding and discharging valve 17, a propellant concentration test port 18, a tank management self-locking valve 19 and a liquid circuit test port 24; the discharge mode includes a propellant discharge self-locking valve 20, a propellant discharge check valve 21 and a filter 22; the blow-off module includes a blow-off electric explosion valve 12 and a blow-off check valve 13; the engine module includes an engine management self-locking valve 14 and an attitude control engine 23.

[0036] like Figure 1 As shown, the gas cylinder 1 is manufactured using a metal lining and composite material winding method. It is mounted on the spacecraft via supports and straps. Other components are integrated into the spacecraft via modular assembly. Ten attitude control engines 23 are arranged on the spacecraft's outer wall. The gas cylinder 1 is fixed upstream of the inflation valve 2 and pressure sensor 3. The propulsion system is equipped with a high-pressure gas circuit electric explosion valve 4 downstream of the gas cylinder 1. The outlet of the high-pressure gas circuit electric explosion valve 4 is connected to the high-pressure gas circuits of the environmental control system and the recovery system, achieving an integrated design for the high-pressure gas supply for propulsion, environmental control, and recovery. High-purity nitrogen is used for the high-pressure gas in all three systems. The high-pressure gas circuit electric explosion valve 4 and the gas circuit high-pressure self-locking valve 5 are connected in sequence between the inflation valve 2 and the high-pressure test port 6. Downstream of the high-pressure test port 6 is a pressure reducing valve 7. Downstream of the pressure reducing valve 7 is a low-pressure test port 8 and the gas circuit low-pressure self-locking valve 9. Downstream of the gas circuit low-pressure self-locking valve 9 are connected to the gas circuit transverse self-locking valve 10, pressure sensor 3, safety valve 11, and purge electric explosion valve 12, respectively. Preferably, a blow-off electric explosion valve 12 and a blow-off one-way valve 13 are connected in series downstream of the low-pressure self-locking valve 9 of the gas circuit. Before the spacecraft lands on the ground, the blow-off electric explosion valve 12, the engine management self-locking valve 14 and the engine are opened to blow off the engine, ensuring that the engine and the liquid pipeline are clean, and setting favorable conditions for subsequent testing before reuse. The downstream of the blow-off electric explosion valve 12 is connected to the blow-off check valve 13, and the downstream of the blow-off check valve 13 is connected to the inlet of the engine management self-locking valve 14 and the outlet of the tank management self-locking valve 19. The downstream of the safety valve 11 is connected to the tank gas end adding and discharging valve 15 and the inlet of the tank 16. The downstream of the tank 16 is connected to the tank liquid end adding and discharging valve 17, the tank management self-locking valve 19 and the pressure sensor 3. The propellant concentration test port 18 is integrated on the tank 16. The upstream of the tank management self-locking valve 19 is connected to the outlet of the tank 16. The downstream of the tank management self-locking valve 19 is connected to the liquid circuit test port 24, the engine management self-locking valve 14 and the inlet of the propellant discharge self-locking valve 20. The downstream of the propellant discharge self-locking valve 20 is connected to the propellant discharge check valve 21. The outlet of the propellant discharge check valve 21 is installed with a filter 22. The downstream of the engine management self-locking valve 14 is connected to the attitude control engine 23. Pressure sensors 3 are mounted between gas cylinder 1 and charging valve 2, gas line low-pressure latching valve 9 and gas line lateral latching valve 10, and tank liquid end charging and discharging valve 17 and tank management latching valve 19. Close high-pressure latching valve 5 and low-pressure latching valve 9, introduce high-pressure nitrogen at a specified flow rate and pressure into high-pressure test port 6, and discharge decompressed nitrogen from low-pressure test port 8 to test the outlet pressure of pressure reducing valve 7.

[0037] The tank of the manned spacecraft reusable propulsion system of the application adopts vacuum filling method to fill 120kg of HAN-based propellant. The high-pressure gas supply, the environmental control system and the recovery system adopt an integrated design scheme, the gas cylinder is filled with nitrogen, and the filling pressure is 35MPa. Before the spacecraft is launched, the propulsion system is set to the initial state, the valve and the engine are set to the initial state, and the pressure sensor 3 is in the powered telemetry monitoring state. Before the spacecraft returns to the earth, the engine catalyst bed is heated and started, then the electromagnetic valve is powered on, and then the engine management self-locking valve 14 and the four 400N attitude control engines 23 are sequentially opened for pipeline vacuum bleeding. After the vacuum bleeding is completed, the engine management self-locking valve 14 and the attitude control engine 23 are closed. Then the gas path high-pressure self-locking valve 5 and the gas path low-pressure self-locking valve 9 are opened to pressurize the tank 16. After the pressurization is completed, the tank management self-locking valve 19 and the engine management self-locking valve 14 are opened to fill the propellant pipeline. The engine has the ignition working condition. During the spacecraft returning to the earth, the engine is ignited according to the GNC command to perform the pitch, yaw and roll attitude control function. Before the spacecraft lands on the ground, the gas path self-locking valve (the gas path high-pressure self-locking valve 5, the gas path low-pressure self-locking valve 9 and the gas path transverse self-locking valve 10) is closed, the propellant discharge self-locking valve 20 is opened to discharge the remaining propellant, and then the blow-off electric explosion valve 12 and the ten attitude control engines 23 are opened to blow off the engine.

[0038] After the spacecraft lands, the propulsion system is visually inspected, the attitude control engine 23 is removed, and the engine catalyst state and engine integrity are checked. The tank 16 and the liquid path pipeline are cleaned, blown off and dried on the spacecraft, and the on-line venting performance of the pressure reducing valve 7 is checked. After the engine is checked and repaired, the attitude control engine 23 is installed on the spacecraft again, and the system airtightness check, electrical performance test, gas filling and propellant filling of the integrated propulsion system are carried out. The propulsion system has the capability of being reused and can perform the flight test mission again.

[0039] The propulsion system opening part is designed to avoid the entry of excess material into the system during the launch process and the landing process on the ground. The propellant discharge port and the attitude control engine 23 nozzle are designed to avoid the entry of excess material into the system during the launch process and the landing process on the ground. The propellant discharge port adopts the combination of a propellant discharge check valve 21 and a filter 22 to prevent excess material from entering the interior of the propulsion system during the spacecraft landing process on the ground, as shown in Figure 4 The attitude control engine 23 nozzle adopts the method of pasting a single-sided adhesive polyimide film. The diameter of the polyimide film is 4mm larger than that of the engine nozzle. The polyimide film is pasted to the outer wall of the attitude control engine 23 nozzle through the circumferential outside circle and a 12mm*10mm square handle to protect the inner cavity of the attitude control engine 23 during the spacecraft launch stage and the launch process, and to prevent raindrops and moisture from entering the attitude control engine 23, as shown in Figure 5The propelling system can discharge the remaining propellant before the spacecraft returns to the landing surface, ensuring the safety of the spacecraft during landing. The propelling system can blow off the attitude control engine 23 before the spacecraft returns to the landing surface, ensuring the cleanliness of the attitude control engine 23.

[0040] More specifically, the specific implementation technical indicators are:

[0041] Engine configuration and thrust requirement: 10 attitude control engines 23 with a thrust of 400N are configured;

[0042] Working medium: gas path: helium (N2), liquid path: HAN-based propellant;

[0043] Propellant filling amount: ≥120kg@15°C (i.e. 120kg at 15°C temperature condition);

[0044] Power consumption: engine pulse peak power consumption ≤50W; heating peak power consumption: ≤100W;

[0045] System working mode: maximum working mode 7 engines are started at the same time, minimum working mode 1 engine is started.

[0046] The tank 16 has the ability to perform online cleaning, drying, and detection on the spacecraft after the spacecraft returns to the ground, and can continue to fill propellant and be reused after passing the detection. The tank 16 uses a combination of a metal shell and a capsule liner, with propellant stored inside the capsule and propellant extrusion gas stored between the capsule outside and the metal shell. The gas end of the tank 16 is provided with a gas path interface and a liquid path interface, the gas path interface of the gas end is connected with the gas inlet pipe of the tank 16, the liquid path interface of the gas end is connected with the tank gas end filling and draining valve 15, the liquid path interface of the liquid end is connected with the tank liquid end filling and draining valve 17, and the gas path interface of the liquid end is connected with the propellant concentration test port 18. After the spacecraft returns to the earth, the tank is filled, the cleaning liquid is discharged, and the drying gas is discharged through the tank gas end filling and draining valve 15 and the tank liquid end filling and draining valve 17, realizing online cleaning and drying of the tank. By opening the propellant concentration test port 18, the propellant concentration outside the tank capsule can be tested to confirm whether the leakage rate of the tank capsule meets the reuse requirements, such as Figure 2 as shown.

[0047] The attitude control engine 23 has the ability to be disassembled, detected, and maintained on the spacecraft after the spacecraft returns to the earth, and can be installed on the spacecraft again after passing the detection and maintenance, realizing reuse. The attitude control engine 23 adopts a 24-degree ball head thread connection and has the ability to be repeatedly disassembled and assembled. After the engine is disassembled, the integrity of the catalyst is detected by CT or X-ray. After the catalyst is detected, the sealing property and leakage rate characteristics of the attitude control engine 23 are confirmed by leakage rate inspection and engine electromagnetic valve action inspection. After inspection and maintenance, the attitude control engine 23 is installed on the spacecraft again, realizing reuse.

[0048] The liquid path pipeline downstream of the tank management self-locking valve 19 has the ability of online cleaning, blowing and drying on the spacecraft after the spacecraft returns to the ground, and the liquid path pipeline after processing can be subjected to various tests such as air tightness. After the attitude control engine 23 is removed, the tank management self-locking valve 19 is closed, cleaning liquid, alcohol and hot nitrogen gas are introduced from the liquid path test port 24, and are discharged from the connection of the ten attitude control engine 23 inlet pipelines and the outlet of the liquid discharge one-way valve 21 respectively, and the cleaning liquid, alcohol and hot nitrogen gas are repeatedly washed for no less than 3 times.

[0049] After the spacecraft returns to the ground for detection and maintenance, the propulsion system has the ability of air tightness detection, electrical performance test and pressure reducing valve performance test on the spacecraft, and the propulsion system has the ability of reuse after the test is qualified. The test process and test method of the air tightness detection and electrical performance test of the propulsion system are the same as the first test of the propulsion system; the pressure reducing valve performance test first closes the air path high pressure self-locking valve 5 and the air path low pressure self-locking valve 9 upstream and downstream of the pressure reducing valve, then uses the ground test equipment and pipeline to introduce high pressure nitrogen gas with specified flow and pressure from the high pressure test port 6, and discharges the reduced pressure nitrogen gas from the low pressure test port 8 and tests the outlet pressure, and the two pressure reducing valves are tested respectively, as shown in Figure 3 .

[0050] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0051] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. A reusable propulsion system for a manned spacecraft, characterized in that: It includes a gas cylinder module, a tank module, a gas circuit test module, a purge module, an exhaust module and an engine module. The gas cylinder module is connected downstream to a gas circuit valve module, which is respectively connected to the tank module and the purge module. The tank module is connected downstream to the exhaust module, and the purge module, the tank module and the exhaust module are respectively connected to the engine module. Before the spacecraft returns, the gas cylinder module pressurizes the tank module through the gas path valve module; before the spacecraft lands, the propellant is discharged through the discharge module, and the engine module is purged by the purge module; after the spacecraft lands, the tank module is cleaned, dried, and purged, the gas path valve module undergoes a pressure relief valve performance test, and the engine module undergoes inspection and maintenance, thereby enabling system reuse. The gas cylinder module comprises a gas cylinder (1), a gas filling valve (2), and a pressure sensor (3), wherein the gas cylinder (1) is fixed upstream of the gas filling valve (2) and the pressure sensor (3); The gas circuit valve module comprises a gas circuit high-pressure electric explosion valve (4), a gas circuit high-pressure self-locking valve (5), a high-pressure test port (6), a pressure reducing valve (7), a low-pressure test port (8) and a gas circuit low-pressure self-locking valve (9); the gas circuit high-pressure electric explosion valve (4) and the gas circuit high-pressure self-locking valve (5) are sequentially connected between the inflation valve (2) and the high-pressure test port (6); the pressure reducing valve (7) is connected downstream of the high-pressure test port (6); the pressure reducing valve (7) is connected downstream of the low-pressure test port (8) and the gas circuit low-pressure self-locking valve (9); the gas circuit low-pressure self-locking valve (9) is respectively connected downstream to the gas circuit lateral self-locking valve (10), the pressure sensor (3), the tank module and the blow-off module; The tank module comprises a safety valve (11), a tank gas end addition and discharge valve (15), a tank (16), a tank liquid end addition and discharge valve (17), a propellant concentration test port (18), a tank management self-locking valve (19), and a liquid circuit test port (24); the upstream of the safety valve (11) is connected to the gas circuit low-pressure self-locking valve (9); the downstream of the safety valve (11) is connected to the tank gas end addition and discharge valve (15) and the inlet of the tank (16); the downstream of the tank (16) is connected to the tank liquid end addition and discharge valve (17), the tank management self-locking valve (19), and the pressure sensor (3); the propellant concentration test port (18) is integrated on the tank (16); the upstream of the tank management self-locking valve (19) is connected to the outlet of the tank (16); the downstream of the tank management self-locking valve (19) is connected to the liquid circuit test port (24), the discharge module, and the engine module; The blow-off module comprises a blow-off electric explosion valve (12) and a blow-off one-way valve (13); the upstream of the blow-off electric explosion valve (12) is connected to the gas path low-pressure self-locking valve (9); the downstream of the blow-off electric explosion valve (12) is connected to the blow-off one-way valve (13); the downstream of the blow-off one-way valve (13) is connected to the inlet of the engine management self-locking valve (14) in the engine module and the outlet of the tank management self-locking valve (19); the downstream of the engine management self-locking valve (14) is connected to the attitude control engine (23) in the engine module.

2. The reusable propulsion system for manned spacecraft according to claim 1, characterized in that: The engine module adopts green and non-toxic HAN-based propellant.

3. The reusable propulsion system for manned spacecraft according to claim 1, characterized in that: The gas circuit high-pressure self-locking valve (5) and the gas circuit low-pressure self-locking valve (9) are closed, high-pressure nitrogen of a specified flow rate and pressure is introduced into the high-pressure test port (6), and the decompressed nitrogen is discharged from the low-pressure test port (8), and the outlet pressure of the pressure reducing valve (7) is tested.

4. The reusable propulsion system for a manned spacecraft according to claim 1, characterized in that: The discharge module includes a propellant discharge self-locking valve (20), a propellant discharge one-way valve (21) and a filter (22). The downstream of the tank management self-locking valve (19) is connected to the inlet of the propellant discharge self-locking valve (20), and the downstream of the propellant discharge self-locking valve (20) is connected to the propellant discharge one-way valve (21). The filter (22) is installed at the outlet of the propellant discharge one-way valve (21).

5. The reusable propulsion system for a manned spacecraft according to claim 1, characterized in that: The nozzle of the attitude control engine (23) is made of a polyimide film with a single-sided adhesive. The diameter of the polyimide film is 4 mm larger than the nozzle of the engine. The polyimide film is adhered to the outer wall of the nozzle of the engine through the outer circle and the 12 mm*10 mm square handle.

6. The reusable propulsion system for a manned spacecraft according to claim 1, characterized in that: The pressure sensor (3) is fixed between the gas cylinder (1) and the charging valve (2), the gas circuit low-pressure self-locking valve (9) and the gas circuit lateral self-locking valve (10), and the tank liquid end filling and discharging valve (17) and the tank management self-locking valve (19).

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