High-pressure gas circuit electronic pressure relief device for satellite

Abstract

According to the high-pressure gas circuit electronic pressure relief device for the satellite, an inlet of a first stop valve is connected with a gas outlet of a high-pressure gas storage device, meanwhile, the inlet of the first stop valve is connected with an inlet of a bypass stop valve, and a gas outlet of a high-pressure pressure sensor is connected with a gas outlet of the high-pressure gas storage device; the first stop valve is used for measuring the pressure of high-pressure gas in the high-pressure gas storage device and controlling the pressure relief pressure, an outlet of the first stop valve is connected with an inlet of the second stop valve, an outlet of the second stop valve is connected with an inlet of the one-way valve, and meanwhile, an outlet of the second stop valve is connected with an outlet of the bypass stop valve; an outlet of the one-way valve is connected with an inlet of the high-pressure gas filter, an outlet of the high-pressure filter is connected with an inlet of the gas balance discharging device, and the gas balance discharging device is used for discharging gas in the high-pressure gas storage device into the air in a zero-thrust mode, so that interference to the attitude of the spacecraft is reduced. According to the high-pressure gas storage device, controllable, rapid and interference-free pressure relief emission of gas in the high-pressure gas storage device can be realized.

Description

Technical Field

[0001] The present invention relates to an electronic relief device for a high-pressure gas storage device used on a satellite, and belongs to the technical field of spacecraft propulsion systems. Background Art

[0002] Generally, high-pressure gas storage devices are included in spacecraft bi-propellant propulsion systems, high-pressure cold gas propulsion systems, and electric propulsion systems, and the high-pressure gas required for the operation of the propulsion system is stored inside.

[0003] At the end of the mission of the spacecraft, for safety considerations, the spacecraft needs to be passivated. The propellants and high-pressure gases with potential safety hazards inside the spacecraft need to complete the pressure relief operation to ensure that the spacecraft will not explode and disintegrate in orbit.

[0004] In the current design of the propulsion system, at the end of the lifespan of the spacecraft, generally, the thruster set at the most downstream of the propulsion system is used to complete the pressure relief operation of the high-pressure gas in the high-pressure gas storage device. Such pressure relief operations have problems such as long pressure relief time, large interference torque on the spacecraft, and many operating components. Summary of the Invention

[0005] The technical problem to be solved by the present invention is: to overcome the deficiencies of the prior art, and provide a device for electronically relieving the high-pressure gas in a high-pressure gas storage device for a satellite, which can quickly complete the pressure relief operation of the high-pressure gas storage device, and can complete the function through closed-loop control to quickly adjust the pressure in the high-pressure storage device.

[0006] The technical solution adopted by the present invention is:

[0007] An electronic pressure relief device for a high-pressure gas path of a satellite includes a first shut-off valve, a second shut-off valve, a high-pressure pressure sensor, a check valve, a high-pressure gas filter, a gas balance discharge device, and a control unit;

[0008] The intake ports of the first shut-off valve and the high-pressure pressure sensor are both connected to the outlet of the high-pressure gas storage device. The outlet of the first shut-off valve is connected to the intake port of the second shut-off valve. The outlet of the second shut-off valve is connected to the intake port of the check valve. The outlet of the check valve is connected to the intake port of the high-pressure gas filter. The outlet of the high-pressure gas filter is connected to the inlet of the gas balance discharge device. The outlet of the gas balance discharge device is arranged on the outer surface of the spacecraft for the rapid diffusion of the gas discharged by pressure relief, and the gas to be pressure-relieved is discharged into the air with zero thrust to reduce the attitude interference on the spacecraft. The control unit is used to control the opening and closing of the first shut-off valve and the second shut-off valve. The control unit is connected to the first shut-off valve, the second shut-off valve, the bypass shut-off valve, and the high-pressure pressure sensor in the device through a cable.

[0009] Further, it further includes a bypass shut-off valve. The air inlet of the bypass shut-off valve is connected to the air inlet of the first shut-off valve, and the air outlet of the bypass shut-off valve is connected to the air inlet of the check valve.

[0010] Further, the first shut-off valve and the second shut-off valve use electric control valves and are opened and closed under the control of the control unit. After the first shut-off valve is powered off, the position of the valve core can be self-held. After the second shut-off valve is powered off, the position of the valve core cannot be self-held.

[0011] Further, the bypass shut-off valve uses an electric control valve and is opened and closed through the control of the control unit. After the bypass shut-off valve is powered off, the position of the valve core can be self-held.

[0012] Further, the first shut-off valve, the second shut-off valve, the high-pressure pressure sensor, the check valve, the high-pressure gas filter, and the gas balance discharge device are connected into a system through pipelines. The pipelines are connected by welding or by using a hard seal method of metal ball head - metal conical surface screw connection.

[0013] Further, the types of gas medium propellants discharged by the pressure relief device include helium, nitrogen, xenon, hydrogen, or oxygen. At the same time, the pressure relief device can also be used for the evacuation treatment of liquid propellants in the spacecraft propulsion system.

[0014] Further, the pressure relief device includes four pressure relief methods. The first pressure relief method is specifically as follows:

[0015] Determine the pressure in the high-pressure gas storage device through the high-pressure pressure sensor. The pressure range that can be electronically relieved in the present invention is 0 - 60 MPa;

[0016] Send an open command for the first shut-off valve through the control unit to open the first shut-off valve;

[0017] Send an open command for the second shut-off valve through the control unit to open the second shut-off valve, and always keep the second shut-off valve in the powered-on open state. The high-pressure gas in the high-pressure gas storage device is discharged to the outside of the spacecraft through the check valve, the high-pressure gas filter, and the gas balance discharge device;

[0018] Monitor the pressure data of the high-pressure pressure sensor;

[0019] When the pressure value of the high-pressure pressure sensor reaches the required pressure value after the high-pressure gas storage device is pressure-relieved, send a close command for the second shut-off valve through the control unit to close the second shut-off valve, and always keep the second shut-off valve in the powered-off closed state. The high-pressure gas in the high-pressure gas storage device stops discharging to the outside of the spacecraft;

[0020] Through the control unit, send a first cut-off valve closing instruction to close the first cut-off valve, further cutting off the passage for the high-pressure gas in the high-pressure gas storage device to be discharged to the outside.

[0021] Furthermore, the second pressure relief method is specifically as follows:

[0022] Determine the pressure in the high-pressure gas storage device through the high-pressure pressure sensor;

[0023] Through the control unit, send a first cut-off valve opening instruction to open the first cut-off valve;

[0024] Through the control unit, send a second cut-off valve pulse working instruction to set the switching cycle of the second cut-off valve as t on = 100 ms, t off = 100 ms, and keep the second cut-off valve in the pulse switch output mode all the time. The high-pressure gas in the high-pressure gas storage device is pulsed out of the spacecraft through the one-way valve, high-pressure gas filter and gas balance discharge device;

[0025] Monitor the pressure data of the high-pressure pressure sensor;

[0026] When the pressure value of the high-pressure pressure sensor reaches the required pressure value after the pressure relief of the high-pressure gas storage device, through the control unit, send a second cut-off valve closing instruction to close the second cut-off valve, and keep the second cut-off valve in the power-off closed state all the time. The high-pressure gas in the high-pressure gas storage device stops being discharged to the outside of the spacecraft;

[0027] Through the control unit, send a first cut-off valve closing instruction to close the first cut-off valve, further cutting off the passage for the high-pressure gas in the high-pressure gas storage device to be discharged to the outside.

[0028] The third pressure relief method is specifically as follows:

[0029] Determine the pressure in the high-pressure gas storage device through the high-pressure pressure sensor;

[0030] Through the control unit, send an alternating pulse switch instruction for the first cut-off valve and the second cut-off valve. The alternating pulse sequence is: t21 on = 100 ms, t21 off = 200 ms, t22 on = 100 ms, t22 off = 200 ms,...; where, t21 on and t21 off are instructions for the first cut-off valve, and t22 on and t22 off are instructions for the second cut-off valve;

[0031] The high-pressure gas in the high-pressure gas storage device is pulsed out of the spacecraft through a one-way valve, a high-pressure gas filter, and a gas balance discharge device;

[0032] The control unit collects the pressure data of the high-pressure pressure sensor in real time;

[0033] When the pressure value of the high-pressure pressure sensor reaches the required pressure value after the high-pressure gas storage device is depressurized, the control unit sends a second shut-off valve closing instruction to close the second shut-off valve, and always keeps the second shut-off valve in a power-off closed state, and the high-pressure gas in the high-pressure gas storage device stops discharging to the outside of the spacecraft.

[0034] The fourth pressure relief method is specifically as follows:

[0035] Determine the pressure in the high-pressure gas storage device through the high-pressure pressure sensor;

[0036] Through the control unit, send a bypass shut-off valve opening instruction to open the bypass shut-off valve;

[0037] The high-pressure gas in the high-pressure gas storage device flows through the bypass shut-off valve and is pulsed out of the spacecraft through a one-way valve, a high-pressure gas filter, and a gas balance discharge device;

[0038] Monitor the pressure data of the high-pressure pressure sensor;

[0039] When the pressure value of the high-pressure pressure sensor reaches the required pressure value after the high-pressure gas storage device is depressurized, through the control unit, send a bypass shut-off valve closing instruction to close the bypass shut-off valve, and the high-pressure gas in the high-pressure gas storage device stops discharging to the outside of the spacecraft.

[0040] The beneficial effects of the present invention compared with the prior art are:

[0041] (1). The high-pressure gas path electronic pressure relief device proposed by the present invention adopts a method of directly relieving pressure from the outlet of the high-pressure gas storage device, and can quickly complete the pressure relief operation of the high-pressure gas in the high-pressure gas storage device;

[0042] (2). The high-pressure gas path electronic pressure relief device proposed by the present invention reduces the operations on the pressure reducer, shut-off valve, thruster, etc. in the propulsion system. Only the opening and closing operations of the first shut-off valve, the second shut-off valve or the bypass shut-off valve need to be completed to complete the pressure relief operation of the high-pressure gas. The pressure relief process is more concise, reducing the failure rate of the system.

[0043] (3). The high-pressure gas path electronic pressure relief device proposed by the present invention, by setting a gas balance discharge device, makes the combined thrust after the high-pressure gas is discharged from the spacecraft close to "zero", and compared with discharging through the thruster arranged at the end of the propulsion system, the interference torque on the spacecraft is smaller.

[0044] (4) The high-pressure gas path electronic pressure relief device proposed by the present invention can set different pressure requirements in the high-pressure gas storage device as required. After completing the electronic pressure relief operation, it will not affect the normal flight mission of the spacecraft.

[0045] (5) The high-pressure gas path electronic pressure relief device proposed by the present invention can also be used as a low-pressure safety relief valve downstream of the system pressure reducer or for propellant passivation evacuation on the storage tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 is the schematic diagram of the high-pressure gas path electronic pressure relief device;

[0047] Figure 2 is the control timing schematic diagram of the first stop valve and the second stop valve. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0048] The present invention will be further described below in conjunction with embodiments.

[0049] As Figure 1 and Figure 2 shown, a high-pressure gas path electronic pressure relief device for a satellite proposed by the present invention includes a first stop valve 21, a second stop valve 22, a high-pressure pressure sensor 24, a check valve 25, a high-pressure gas filter 26, a gas balance discharge device 27, and a control unit 3;

[0050] In the high-pressure gas path electronic pressure relief device 2, the inlet of the first stop valve 21 is connected to the outlet of the high-pressure gas storage device 1, the inlet of the bypass stop valve 23 is connected to the outlet of the high-pressure gas storage device 1 in the high-pressure cold gas propulsion system, the inlet of the high-pressure pressure sensor 24 is connected to the outlet of the high-pressure gas storage device 1 in the high-pressure cold gas propulsion system, the outlet of the first stop valve 21 is connected to the inlet of the second stop valve 22, the outlet of the second stop valve 22 is connected to the inlet of the check valve 25. At the same time, the inlet of the check valve 25 is connected to the outlet of the bypass stop valve 23, the outlet of the check valve 25 is connected to the inlet of the high-pressure gas filter 26, the outlet of the high-pressure gas filter 26 is connected to the inlet of the gas balance discharge device 27, and the outlet of the gas balance discharge device 27 is arranged on the outer surface of the aircraft, which is conducive to the rapid diffusion of the pressure-relieved gas, discharging the gas to be pressure-relieved into the air with zero thrust, and reducing the attitude interference to the spacecraft. The control unit 3 is connected to the first stop valve 21, the second stop valve 22, the bypass stop valve 23, and the high-pressure pressure sensor 24 in the device through cables.

[0051] Preferably, it further includes a bypass stop valve 23. The inlet of the bypass stop valve 23 is connected to the inlet of the first stop valve 21, and the outlet of the bypass stop valve 23 is connected to the inlet of the check valve 25.

[0052] Preferably, the first shut-off valve 21 and the second shut-off valve 22 are electrically controlled valves, and their opening and closing are realized under the control of the control unit 3;

[0053] The first shut-off valve 21 is selected as a self-locking valve product whose spool position can be self-maintained after power-off.

[0054] The second shut-off valve 22 is selected as a solenoid valve product whose spool position cannot be self-maintained after power-off.

[0055] The bypass shut-off valve 23 is selected as a self-locking valve product whose spool position can be self-maintained after power-off or a high-voltage electric explosion valve product.

[0056] Preferably, the components in the high-pressure gas path electronic pressure relief device 2 are connected into a system through pipelines, and the pipelines are connected by welding or by using a hard seal method of metal ball head - metal conical surface screw connection.

[0057] The types of gases that the high-pressure gas path electronic pressure relief device 2 can discharge include common gas medium propellants such as "helium", "nitrogen", "xenon", "hydrogen", "oxygen", etc. in the spacecraft propulsion system. At the same time, this set of electronic pressure relief device can also be used for the evacuation treatment of liquid propellants in the spacecraft propulsion system, and the types of liquids discharged include common liquid propellants such as "anhydrous hydrazine", "monopropellant - 3", "ADN", "HAN", "nitrogen tetroxide", "methyl hydrazine", "unsymmetrical dimethylhydrazine", "liquid ammonia", "liquid hydrogen", "liquid oxygen", "methane", "kerosene", etc. in the spacecraft propulsion system.

[0058] The high-pressure gas path electronic pressure relief device 2 includes four pressure relief working modes.

[0059] The first working mode is as follows:

[0060] 1) Determine the pressure in the high-pressure gas storage device 1 through the high-pressure pressure sensor 24. The pressure range that can be electronically pressure-relieved in the present invention is 0 - 60 MPa;

[0061] 2) Through the control unit 3, send an open command for the first shut-off valve 21 to open the first shut-off valve 21;

[0062] 3) Through the control unit 3, send an open command for the second shut-off valve 22 to open the second shut-off valve 22, and always keep the second shut-off valve 22 in the powered-on open state. The high-pressure gas in the high-pressure gas storage device 1 is discharged to the outside of the spacecraft through the one-way valve 25, the high-pressure gas filter 26, and the gas balance discharge device 27;

[0063] 4) Monitor the pressure data of the high-pressure pressure sensor 24;

[0064] 5) When the pressure value of the high-pressure pressure sensor 24 reaches the required pressure value after the high-pressure gas storage device 1 is depressurized, the control unit 3 sends a second cut-off valve 22 closing instruction to close the second cut-off valve 22, and keeps the second cut-off valve 22 in the power-off closed state all the time. The high-pressure gas in the high-pressure gas storage device 1 stops discharging to the outside of the spacecraft;

[0065] 6) The control unit 3 sends a first cut-off valve 21 closing instruction to close the first cut-off valve 21,

[0066] further cutting off the channel for the high-pressure gas in the high-pressure gas storage device 1 to discharge to the outside; The second working mode is as follows:

[0067] 1) Determine the pressure in the high-pressure gas storage device 1 through the high-pressure pressure sensor 24. The pressure range that can be electronically depressurized in the present invention is 0-60 MPa;

[0068] 2) The control unit 3 sends a first cut-off valve 21 opening instruction to open the first cut-off valve 21;

[0069] 3) The control unit 3 sends a second cut-off valve 22 pulse working instruction to set the switching period of the second cut-off valve

[0070] 22 to t on = 100 ms, t off = 100 ms, and keep the second cut-off valve

[0071] 22 always in the pulse switch output mode. The high-pressure gas in the high-pressure gas storage device 1 is pulsed out of the spacecraft through the one-way valve 25, the high-pressure gas filter 26 and the gas balance discharge device 27;

[0072] 4) Monitor the pressure data of the high-pressure pressure sensor 24;

[0073] 5) When the pressure value of the high-pressure pressure sensor 24 reaches the required pressure value after the high-pressure gas storage device 1 is depressurized, the control unit 3 sends a second cut-off valve 22 closing instruction to close the second cut-off valve 22, and keeps the second cut-off valve 22 in the power-off closed state all the time. The high-pressure gas in the high-pressure gas storage device 1 stops discharging to the outside of the spacecraft;

[0074] 6) The control unit 3 sends a first cut-off valve 21 closing instruction to close the first cut-off valve 21,

[0075] further cutting off the channel for the high-pressure gas in the high-pressure gas storage device 1 to discharge to the outside; The third working mode is as follows:

[0076] 1) Determine the pressure inside the high-pressure gas storage device 1 through the high-pressure pressure sensor 24. The pressure range that can be electronically relieved in the present invention is 0 to 60 MPa;

[0077] 2) Through the control unit, send alternating pulse switch commands to the first shut-off valve 21 and the second shut-off valve 22. The alternating pulse sequence is t21 on = 100 ms, t21 off = 200 ms, t22 on = 100 ms,

[0078] t22 off = 200 ms………;

[0079] 3) The high-pressure gas inside the high-pressure gas storage device 1 is pulsed out of the spacecraft through the one-way valve 25, the high-pressure gas filter 26, and the gas balance discharge device 27;

[0080] 4) The control unit collects the pressure data of the high-pressure pressure sensor 24 in real time;

[0081] 5) When the pressure value of the high-pressure pressure sensor 24 reaches the required pressure value after the high-pressure gas storage device 1 is depressurized, the control unit sends a closing command to the second shut-off valve 22 to close the second shut-off valve 22, and always keeps the second shut-off valve 22 in the power-off closed state, and the high-pressure gas inside the high-pressure gas storage device 1 stops discharging to the outside of the spacecraft;

[0082] 6) The control unit sends a closing command to the first shut-off valve 21 to close the first shut-off valve 21, further cutting off the channel for the high-pressure gas inside the high-pressure gas storage device 1 to discharge to the outside;

[0083] The fourth working mode is as follows:

[0084] 1) Determine the pressure inside the high-pressure gas storage device 1 through the high-pressure pressure sensor 24. The pressure range that can be electronically relieved in the present invention is 0 to 60 MPa;

[0085] 2) Through the control unit 3, send an opening command to the bypass shut-off valve 23 to open the bypass shut-off valve 23;

[0086] 3) The high-pressure gas inside the high-pressure gas storage device 1 flows through the bypass shut-off valve 23 and is pulsed out of the spacecraft through the one-way valve 25, the high-pressure gas filter 26, and the gas balance discharge device 27;

[0087] 4) Monitor the pressure data of the high-pressure pressure sensor 24;

[0088] 5) When the pressure value of the high-pressure pressure sensor 24 reaches the required pressure value after the high-pressure gas storage device 1 relieves pressure, through the control unit 3, a bypass cut-off valve 23 closing instruction is sent to close the bypass cut-off valve 23, and the high-pressure gas in the high-pressure gas storage device 1 stops discharging to the outside of the spacecraft;

[0089] 6) When it is necessary to passivate the high-pressure gas in the propulsion system during orbit operation, finally keep the bypass cut-off valve 23 always in the open state to ensure that the high-pressure gas in the high-pressure gas storage device 1 can be completely emptied.

[0090] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A high-pressure gas circuit electronic pressure relief device for satellites, characterized in that: It comprises a first stop valve (21), a second stop valve (22), a high-pressure pressure sensor (24), a one-way valve (25), a high-pressure gas filter (26), a gas balance exhaust device (27) and a control unit (3); The air inlets of the first stop valve (21) and the high-pressure pressure sensor (24) are both connected to the air outlet of the high-pressure gas storage device (1); the air outlet of the first stop valve (21) is connected to the air inlet of the second stop valve (22); the air outlet of the second stop valve (22) is connected to the air inlet of the one-way valve (25); the air outlet of the one-way valve (25) is connected to the air inlet of the high-pressure gas filter (26); the air outlet of the high-pressure gas filter (26) is connected to the inlet of the gas balance exhaust device (27); the air outlet of the gas balance exhaust device (27) is arranged on the outer surface of the aircraft, and is used for the rapid diffusion of the pressure-released exhaust gas; the control unit (3) is used to control the on-off of the first stop valve (21) and the second stop valve (22).

2. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 1, characterized in that: It also includes a bypass stop valve (23), the air inlet of the bypass stop valve (23) is connected to the air inlet of the first stop valve (21), and the air outlet of the bypass stop valve (23) is connected to the air inlet of the one-way valve (25).

3. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 2, characterized in that: The first stop valve (21) and the second stop valve (22) use electrically controlled valves to realize on-off under the control of the control unit (3); the valve core position of the first stop valve (21) can be self-maintained after power is cut off; the valve core position of the second stop valve (22) cannot be self-maintained after power is cut off.

4. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 2, characterized in that: The bypass stop valve (23) uses an electrically controlled valve, which is switched on and off by control of the control unit (3). The valve core position of the bypass stop valve (23) can be self-maintained after the power is cut off.

5. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 1, characterized in that: The first stop valve (21), the second stop valve (22), the high-pressure pressure sensor (24), the one-way valve (25), the high-pressure gas filter (26), and the gas balance discharge device (27) are connected to form a system through pipelines, and the pipelines are connected by welding or by a metal ball head-metal cone surface screw connection hard sealing method.

6. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 1, characterized in that: The types of gaseous propellants discharged by the pressure relief device include helium, nitrogen, xenon, hydrogen or oxygen; at the same time, the pressure relief device can also be used for the emptying treatment of liquid propellants in the propulsion system of a spacecraft.

7. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 3, characterized in that: The pressure relief device includes four pressure relief modes, and the first pressure relief mode is specifically: Determining the pressure in the high-pressure gas storage device (1) by means of a high-pressure pressure sensor (24); Sending a first stop valve (21) opening instruction via a control unit (3) to open the first stop valve (21); A control unit (3) sends a second stop valve (22) opening instruction to open the second stop valve (22), and the second stop valve (22) is kept in an energized open state, so that the high-pressure gas in the high-pressure gas storage device (1) is discharged to the outside of the spacecraft through a one-way valve (25), a high-pressure gas filter (26) and a gas balance discharge device (27); monitoring pressure data of a high pressure pressure sensor (24); When the pressure value of the high-pressure pressure sensor (24) reaches the pressure value required after the high-pressure gas storage device (1) is depressurized, a second stop valve (22) closing instruction is sent through the control unit (3), the second stop valve (22) is closed, and the second stop valve (22) is kept in a power-off closed state, and the high-pressure gas in the high-pressure gas storage device (1) stops being discharged to the outside of the spacecraft; A control unit (3) sends a command to close the first stop valve (21), thereby closing the first stop valve (21) and further cutting off a passage for the high-pressure gas in the high-pressure gas storage device (1) to be discharged to the outside.

8. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 3, characterized in that: The second pressure relief method is as follows: Determining the pressure in the high-pressure gas storage device (1) by means of a high-pressure pressure sensor (24); Sending a first stop valve (21) opening instruction via a control unit (3) to open the first stop valve (21); A control unit (3) sends a pulse operation command to the second stop valve (22), and sets the switch period of the second stop valve (22) to t on =100ms, t off = 100 ms, and the second stop valve (22) is kept in the pulse switch output mode, and the high-pressure gas in the high-pressure gas storage device (1) is discharged to the outside of the spacecraft in a pulsed manner through the one-way valve (25), the high-pressure gas filter (26) and the gas balance discharge device (27); monitoring pressure data of a high pressure pressure sensor (24); When the pressure value of the high-pressure pressure sensor (24) reaches the pressure value required after the high-pressure gas storage device (1) is depressurized, a second stop valve (22) closing instruction is sent through the control unit (3), the second stop valve (22) is closed, and the second stop valve (22) is kept in a power-off closed state, and the high-pressure gas in the high-pressure gas storage device (1) stops being discharged to the outside of the spacecraft; A control unit (3) sends a command to close the first stop valve (21), thereby closing the first stop valve (21) and further cutting off a passage for the high-pressure gas in the high-pressure gas storage device (1) to be discharged to the outside.

9. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 3, characterized in that: The third pressure relief method is as follows: Determining the pressure in the high-pressure gas storage device (1) by means of a high-pressure pressure sensor (24); The control unit sends an alternating pulse switch command to the first stop valve (21) and the second stop valve (22), and the alternating pulse sequence is: t21 on =100ms, t21 off =200ms, t22 on =100ms, t22 off =200ms, ...; where t21 on and t21 off is the command for the first stop valve, t22 on and t22 off is an instruction for the second stop valve; The high-pressure gas in the high-pressure gas storage device (1) is discharged to the outside of the spacecraft in a pulsed manner through a one-way valve (25), a high-pressure gas filter (26) and a gas balance discharge device (27); The control unit collects pressure data of the high-pressure pressure sensor (24) in real time; When the pressure value of the high-pressure pressure sensor (24) reaches the pressure value required after the high-pressure gas storage device (1) is depressurized, the control unit sends a second stop valve (22) closing instruction to close the second stop valve (22), and keeps the second stop valve (22) in a power-off closed state, so that the high-pressure gas in the high-pressure gas storage device (1) stops being discharged to the outside of the spacecraft.

10. The high-pressure gas circuit electronic pressure relief device for satellites according to claim 3, characterized in that: The fourth pressure relief method is as follows: Determining the pressure in the high-pressure gas storage device (1) by means of a high-pressure pressure sensor (24); Sending a bypass stop valve (23) opening instruction via the control unit (3) to open the bypass stop valve (23); The high-pressure gas in the high-pressure gas storage device (1) flows through the bypass stop valve (23) and is discharged to the outside of the spacecraft in a pulsed manner through the one-way valve (25), the high-pressure gas filter (26) and the gas balance discharge device (27); monitoring pressure data of a high pressure pressure sensor (24); When the pressure value of the high-pressure pressure sensor (24) reaches the pressure value required after the high-pressure gas storage device (1) is depressurized, a bypass stop valve (23) closing instruction is sent through the control unit (3), the bypass stop valve (23) is closed, and the high-pressure gas in the high-pressure gas storage device (1) stops being discharged to the outside of the spacecraft.

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