Spacecraft propulsion system and high-operating-state start-up method thereof

Abstract

The present invention relates to a spacecraft propulsion system and a high-operating-condition starting method thereof in the field of spacecraft propulsion technology, comprising: a pressurized gas management module is respectively connected to the inlet of a fuel tank and an oxidant tank through a gas decompression device, a track control engine is respectively connected to the outlet of the fuel tank and the oxidant tank, a fuel gas path unidirectional flow management device and a fuel gas path valve module are sequentially arranged between the gas decompression device and the fuel tank, an oxidant gas path unidirectional flow management device and an oxidant gas path valve module are sequentially arranged in the pipeline between the gas decompression device and the oxidant tank, and pressure sensors are respectively arranged at the outlet of the gas decompression device, the outlet of the oxidant tank, the outlet of the fuel tank, the oxidant inlet of the track control engine and the fuel inlet. The present invention solves the reverse pressure problem of the gas path unidirectional management device in the process of starting the track control engine with conventional constant pressure under the high-temperature and high-pressure working conditions of the tank.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft orbit control technology, and in particular to a method for starting a spacecraft propulsion system and a spacecraft orbit control engine under high system pressure, and in particular to a method for reliable starting under the condition of increased tank pressure of the propulsion system caused by high temperature of the spacecraft. Background Art

[0002] In recent years, with the continuous development of aerospace technology, high requirements have been put forward for the long life and high temperature adaptability of spacecraft. Detectors in the field of deep space exploration, such as my country's asteroid exploration mission and the United States' Venus exploration mission, all have long-term mission profiles in orbit and high temperature of spacecraft. The long-term on-orbit problem puts forward long-life requirements for the propulsion system of spacecraft. For example, the on-orbit flight life of the asteroid exploration mission is as long as 10 years, and the propulsion system needs to reliably manage the low-pressure gas path. Therefore, the common method in the design of the propulsion system is to set up gas path valve modules + one-way flow management devices in the gas paths of the oxidizer and fuel tanks respectively, so as to achieve effective isolation of the gas paths of the oxidizer and fuel tanks, prevent the oxidizer and fuel vapor from mixing and causing explosion, and ensure the long-term reliable and safe low-pressure gas path of the propulsion system in orbit. The high temperature environment of the spacecraft will cause the tank of the propulsion system to face a long-term operating temperature of 30-50℃ or even higher during the flight. The temperature of the tank of a general spacecraft is within 30℃. Therefore, under the limited tank volume, the propellant expands at high temperature, and the tank may face the problem of high pressure caused by high temperature, that is, the pressure of the tank air cushion is higher than the pressure at the outlet of the gas path one-way management device. The orbit control engine of the spacecraft generally adopts the constant pressure orbit change method for starting and ignition, that is, the ignition action is performed when the tank is connected to the pressurized gas path. In the case of high temperature and high pressure in the tank, when the constant pressure ignition is started, the gas path valve management module is opened, which may cause the downstream pressure of the one-way management device to be higher than the upstream pressure, causing reverse pressure. In severe cases, the reverse seal of the one-way management device will fail, which will bring hidden dangers to the long-life orbit of the spacecraft. Therefore, it is necessary to design a method for reliable and safe starting of the propulsion system under high working conditions to address the system high pressure problem caused by high temperature.

[0003] Patent document CN106439494 (application number CN201610822166.0) discloses a satellite propulsion system gas circuit module, which uses a gas circuit valve module + a one-way valve to isolate the propellant vapor upstream of the tank. Patent document CN106134409B (application number: CN201318001673.5) discloses a one-way valve structure, which is widely used in long-life propulsion systems to isolate the propellant vapor in the oxidizer and fuel tank gas circuits, ensuring the long-term safety and reliability of the low-pressure gas circuit of the propulsion system in orbit. The preferred use condition of this valve is not to be reversely pressurized. Summary of the invention

[0004] In view of the defects in the prior art, an object of the present invention is to provide a spacecraft propulsion system and a method for starting the system under high operating conditions.

[0005] A spacecraft propulsion system provided according to the present invention includes a pressurized gas management module, a fuel tank, an oxidizer tank, and a track control engine;

[0006] The pressurized gas management module is communicated with the inlets of the fuel tank and the oxidant tank respectively through a gas decompression device, and the track control engine is communicated with the outlets of the fuel tank and the oxidant tank respectively. A fuel gas path one-way flow management device and a fuel gas path valve module are sequentially arranged between the gas decompression device and the fuel tank, and an oxidant gas path one-way flow management device and an oxidant gas path valve module are sequentially arranged in the pipeline between the gas decompression device and the oxidant tank. A first pressure sensor is arranged at the outlet of the gas decompression device, a second pressure sensor is arranged at the outlet of the oxidant tank, a third pressure sensor is arranged at the outlet of the fuel tank, and a fourth pressure sensor and a fifth pressure sensor are respectively arranged at the oxidant inlet and the fuel inlet of the track control engine;

[0007] When the static pressure value of any one of the second pressure sensor and the third pressure sensor is greater than the static pressure value of the first pressure sensor, the rail control engine first starts ignition through the pressure drop mode, and then switches from the pressure drop mode to the constant pressure mode. The so-called pressure drop mode means that when the rail control engine is ignited and started, the fuel gas circuit valve module and the oxidant gas circuit valve module are in a closed state, and the fuel tank, the oxidant tank and the gas circuit booster module are not connected, and the rail control engine starts ignition.

[0008] In some implementations, the orbital control engine switches the propulsion system operating mode from a drop-pressure mode to a constant-pressure mode by means of an autonomous management program or a delayed instruction.

[0009] In some embodiments, the autonomous management program is used as follows: before the rail control engine is ignited and started, the autonomous management program for the high-operating-condition ignition of the rail control engine is started through a ground injection instruction, and the autonomous management program reads the pressure values ​​of the second pressure sensor, the third pressure sensor, the fourth pressure sensor, and the fifth pressure sensor. When the autonomous management program determines that the pressure values ​​of at least three sensors among the second pressure sensor, the third pressure sensor, the fourth pressure sensor, and the fifth pressure sensor are less than or equal to a set pressure threshold, the autonomous management program controls the opening of the fuel gas circuit valve module and the oxidant gas circuit valve module.

[0010] In some embodiments, the delay instruction is used in the following manner: before the rail control engine is ignited and started, a delay instruction is injected on the ground, and the delay instruction is used to instruct the fuel gas circuit valve module and the oxidant gas circuit valve module to open a predetermined time after the rail control engine is ignited and started in a pressure drop manner.

[0011] The present invention also provides a method for starting a spacecraft propulsion system in a high operating condition, using the spacecraft propulsion system, comprising the following steps:

[0012] S1, judgment of high working condition of propulsion system: before the spacecraft changes orbit, the pressure of the propulsion system is remotely measured and judged by the ground. When the static pressure value of the first pressure sensor is less than that of the second pressure sensor or the static pressure value of the first pressure sensor is less than that of the third pressure sensor, it is judged that the propulsion system is in a high working condition;

[0013] S2, judging the high-operating-condition starting condition of the rail control engine: performing telemetry judgment on the fourth pressure sensor and the fifth pressure sensor on the ground to determine that the static pressure value of the fourth pressure sensor or the fifth pressure sensor does not exceed the preset pressure value of the rail control engine;

[0014] S3, the rail control engine starts ignition in a pressure-reducing manner: after step S1 and step S2, the fuel gas circuit valve module and the oxidant gas circuit valve module close the valves according to the instruction, and the rail control engine starts ignition in a pressure-reducing manner when the fuel tank, the oxidant tank and the pressurized gas management module are isolated;

[0015] S4, switching of the ignition mode of the track control engine: after step S3, along with the ignition start of the track control engine, the ignition mode of the track control engine is switched from the drop pressure mode to the constant pressure mode by adopting an autonomous management program or a delay instruction;

[0016] S5, ignition operation of the track control engine in constant pressure mode: after step S4, when the ignition mode of the track control engine is switched from the pressure drop mode to the constant pressure mode, the fuel gas circuit valve module and the oxidant gas circuit valve module are opened according to the instruction, and the fuel tank, the oxidant tank and the pressurized gas management module are kept in communication, and the track control engine ignites in the constant pressure mode until the track change is completed.

[0017] In some embodiments, in step S4, the autonomous management program is used in the following manner: before the rail control engine is ignited and started, the autonomous management program for the high-operating-condition ignition of the rail control engine is started through a ground injection instruction, and the autonomous management program reads the pressure values ​​of the second pressure sensor, the third pressure sensor, the fourth pressure sensor, and the fifth pressure sensor. When the autonomous management program determines that the pressure values ​​of at least three sensors among the second pressure sensor, the third pressure sensor, the fourth pressure sensor, and the fifth pressure sensor are less than or equal to a set pressure threshold, the autonomous management program controls the opening of the fuel gas circuit valve module and the oxidant gas circuit valve module.

[0018] In some implementations, the pressure threshold can be modified and adjusted in orbit according to ground remote control instructions.

[0019] In some embodiments, the pressure threshold of the second pressure sensor is the difference between the locking pressure of the gas pressure reducing device and the opening pressure of the oxidant gas circuit one-way flow management device; the pressure threshold of the third pressure sensor is the difference between the locking pressure of the gas pressure reducing device and the opening pressure of the fuel gas circuit one-way flow management device; the pressure threshold of the fourth pressure sensor is the pressure value of the second pressure sensor minus the flow resistance of the system pipeline between the oxidant tank and the rail control engine; the pressure threshold of the fifth pressure sensor is the pressure value of the third pressure sensor minus the flow resistance of the system pipeline between the fuel tank and the rail control engine.

[0020] In some embodiments, in step S4, the delay instruction is used in the following manner: before the rail control engine is ignited and started, a delay instruction is injected on the ground, and the delay instruction is used to instruct the fuel gas circuit valve module and the oxidant gas circuit valve module to open a predetermined time after the rail control engine is ignited and started in a pressure drop manner.

[0021] In some implementations, the time set by the delay instruction retains a predetermined margin to ensure that the pressure values ​​of the second pressure sensor and the third pressure sensor are lower than the pressure value of the first pressure sensor.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] The present invention retains the traditional long-life, high-reliability, low-pressure gas path design of the spacecraft propulsion system, while solving the problem of reverse pressure in the gas path one-way management device during the conventional constant-pressure start-up of the orbit control engine caused by the high-temperature mission profile of the spacecraft. This ensures the reliability of orbit change under high operating conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0025] Figure 1 This is the architecture diagram of the spacecraft propulsion system for this application. DETAILED DESCRIPTION

[0026] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments 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 of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0027] Example 1

[0028] This embodiment provides a spacecraft propulsion system, and in particular, a spacecraft orbit control system suitable for high operating conditions, including a pressurized gas management module 1, a fuel tank 7, an oxidizer tank 8, and an orbit control engine 9. Figure 1 As shown, the architecture of the system is:

[0029] The pressurized gas management module 1 is connected to the inlet of the fuel tank 7 and the oxidizer tank 8 through the gas pressure reducing device 2, and is used to inject pressurized gas into the fuel tank 7 and the oxidizer tank 8, and squeeze the propellant in the tank to enter the rail control engine 9 at a predetermined pressure and flow rate. As known in the art, the inlet of the fuel tank 7 and the oxidizer tank 8 refers to the air inlet of the pressurized gas. A first pressure sensor 101 is provided at the gas outlet of the gas pressure reducing device 2. A fuel gas circuit unidirectional flow management device 3 and a fuel gas circuit valve module 5 are provided between the gas pressure reducing device 2 and the fuel tank 7 in sequence. The fuel gas circuit unidirectional flow management device 3 only allows the gas in the pressurized gas management module 1 to enter the fuel tank 7, and prohibits the fuel gas in the fuel tank 7 from flowing toward the pressurized management module 1 under a predetermined pressure. The fuel gas circuit valve module 5 opens and closes the gas circuit according to the instruction, and controls the high-pressure gas in the pressurized gas management module 1 to enter the fuel tank 7 during the corresponding period. An oxidant one-way flow management device 4 and an oxidant gas path valve module 6 are provided in sequence between the gas decompression device 2 and the oxidant tank 8. The oxidant one-way flow management device 4 only allows the gas in the pressurized gas management module 1 to enter the oxidant tank 8, and prohibits the oxidant gas in the oxidant tank 8 from flowing toward the pressurized gas management module 1 under a predetermined pressure. The oxidant valve module 6 opens and closes the gas path according to the instruction, and controls the high-pressure gas in the pressurized gas management module 1 to enter the oxidant tank 8 during the corresponding period. The propellant outlets of the fuel tank 7 and the oxidant tank 8 are respectively connected to the propellant inlet of the track control engine 9. A second pressure sensor 102 is provided at the outlet of the oxidant tank 8. A third pressure sensor 103 is provided at the outlet of the fuel tank 7. A fourth pressure sensor 104 is provided at the oxidant inlet of the track control engine 9. A fifth pressure sensor 105 is provided at the fuel inlet of the track control engine 9.

[0030] The working principle of this embodiment is as follows: before the track control engine 9 is ignited and started, the control system determines whether to open the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6 according to the static pressure value of the first pressure sensor 101 relative to the static pressure value of any one of the second pressure sensor 102 and the third pressure sensor 103. When the static pressure value of any one of the second pressure sensor 102 and the third pressure sensor 103 is higher than that of the first pressure sensor 101, the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6 are closed according to the instruction, and the track control engine 9 starts the ignition by the pressure drop method at this time. After the track control engine 9 starts the ignition by the pressure drop method for a certain period of time, the propulsion system working mode is switched from the pressure drop mode to the constant pressure mode by the autonomous management program or the delayed instruction. In this embodiment, when the tank is at high temperature and high pressure, the orbit control engine is first ignited and started by means of pressure drop, which solves the problem of reverse pressure in the one-way management device of the gas path caused by the high pressure of the propulsion tank due to the high temperature mission profile of the spacecraft, and thus causes the orbit control engine to start during the conventional constant pressure process, thereby ensuring the reliability of orbit change under high working conditions.

[0031] The specific operation of the orbit control engine 9 switching the propulsion system working mode from the pressure drop mode to the constant pressure mode by using the autonomous management program or the delayed instruction is as follows:

[0032] The autonomous management program is as follows: before the orbit control engine 9 is ignited and started, the autonomous management program for the high-operating-condition ignition of the orbit control engine 9 is started through the ground injection command. The autonomous management program reads the pressure values ​​of the second pressure sensor 102, the third pressure sensor 103, the fourth pressure sensor 104, and the fifth pressure sensor 105. When the autonomous management program determines that the pressure values ​​of at least three sensors among the second pressure sensor 102, the third pressure sensor 103, the fourth pressure sensor 104, and the fifth pressure sensor 105 are less than or equal to the set pressure threshold, the autonomous management program controls the opening of the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6. Then, the ignition start of the orbit control engine 9 is switched from the pressure drop mode to the constant pressure mode, and the orbit control engine 9 ignites and works in the constant pressure mode until the orbit change is completed. Among them, the pressure threshold is a reasonable pressure value of the tank and the engine inlet, specifically as follows: the pressure threshold of the second pressure sensor 102 is the difference between the locking pressure of the gas pressure reducing device 2 and the opening pressure of the oxidant gas path one-way flow management device 4; the pressure threshold of the third pressure sensor 103 is the difference between the locking pressure of the gas pressure reducing device 2 and the opening pressure of the fuel gas path one-way flow management device 5, the pressure threshold of the fourth pressure sensor 104 is the pressure value of the second pressure sensor 102 minus the flow resistance of the system pipeline between the oxidant tank 8 and the rail control engine 9, and the pressure threshold of the fifth pressure sensor 105 is the pressure value of the prime third pressure sensor 103 minus the flow resistance of the system pipeline between the fuel tank 7 and the rail control engine 9. In some embodiments, the pressure threshold can be modified and adjusted on the track according to the ground remote control command.

[0033] The delay instruction is as follows: before the rail control engine 9 is ignited and started, a delay instruction is injected on the ground, and the delay instruction is used to instruct the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6 to open after a predetermined time when the rail control engine 9 is ignited and started in a pressure drop manner. The time set by the delay instruction retains a predetermined margin to ensure that the pressure values ​​of the second pressure sensor 102 and the third pressure sensor 103 are lower than the pressure value of the first pressure sensor 101.

[0034] Example 2

[0035] Embodiment 2 is a method for starting a spacecraft propulsion system under high operating conditions based on Embodiment 1, using the spacecraft propulsion system as claimed in claim 1, and comprising the following steps:

[0036] S1, judgment of the high operating state of the propulsion system: before the spacecraft changes its orbit, the propulsion system pressure is remotely measured and judged through the ground. When the static pressure value of the first pressure sensor 101 is less than that of the second pressure sensor 102 or the static pressure value of the first pressure sensor 101 is less than that of the third pressure sensor 103, it is judged that the propulsion system is in a high operating state.

[0037] S2, judging the high-operating-condition starting condition of the rail control engine: by performing telemetry judgment on the fourth pressure sensor 104 and the fifth pressure sensor 105 on the ground, it is determined that the static pressure value of the fourth pressure sensor 104 or the fifth pressure sensor 105 does not exceed the preset pressure value of the rail control engine 9.

[0038] S3, the rail control engine starts ignition by pressure reduction: after step S1 and step S2, the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6 close the valves according to the instructions, and when the fuel tank 7, the oxidant tank 8 and the pressurized gas management module 1 are isolated, the rail control engine 9 starts ignition by pressure reduction.

[0039] S4, switching of the ignition mode of the track control engine: after step S3, along with the ignition start of the track control engine 9, the ignition mode of the track control engine 9 is switched from the drop pressure mode to the constant pressure mode by means of an autonomous management program or a delayed instruction.

[0040] Before the orbit control engine 9 is ignited and started, the autonomous management program for the high-operating-condition ignition of the orbit control engine 9 is started through the ground injection command. The autonomous management program reads the pressure values ​​of the second pressure sensor 102, the third pressure sensor 103, the fourth pressure sensor 104, and the fifth pressure sensor 105. When the autonomous management program determines that the pressure values ​​of at least three sensors among the second pressure sensor 102, the third pressure sensor 103, the fourth pressure sensor 104, and the fifth pressure sensor 105 are less than or equal to the set pressure threshold, the autonomous management program controls the opening of the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6. Then, the ignition start of the orbit control engine 9 is switched from the pressure drop mode to the constant pressure mode, and the orbit control engine 9 ignites and works in the constant pressure mode until the orbit change is completed. Among them, the pressure threshold is a reasonable pressure value of the tank and the engine inlet, specifically as follows: the pressure threshold of the second pressure sensor 102 is the difference between the locking pressure of the gas pressure reducing device 2 and the opening pressure of the oxidant gas path one-way flow management device 4; the pressure threshold of the third pressure sensor 103 is the difference between the locking pressure of the gas pressure reducing device 2 and the opening pressure of the fuel gas path one-way flow management device 5, the pressure threshold of the fourth pressure sensor 104 is the pressure value of the second pressure sensor 102 minus the flow resistance of the system pipeline between the oxidant tank 8 and the rail control engine 9, and the pressure threshold of the fifth pressure sensor 105 is the pressure value of the prime third pressure sensor 103 minus the flow resistance of the system pipeline between the fuel tank 7 and the rail control engine 9. In some embodiments, the pressure threshold can be modified and adjusted on the track according to the ground remote control command.

[0041] The delay instruction is as follows: before the rail control engine 9 is ignited and started, a delay instruction is injected on the ground, and the delay instruction is used to instruct the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6 to open after a predetermined time when the rail control engine 9 is ignited and started in a pressure drop manner. The time set by the delay instruction retains a predetermined margin to ensure that the pressure values ​​of the second pressure sensor 102 and the third pressure sensor 103 are lower than the pressure value of the first pressure sensor 101.

[0042] S5, ignition operation of the track control engine in constant pressure mode: after step S4, when the ignition mode of the track control engine 9 is switched from the pressure drop mode to the constant pressure mode, the fuel gas circuit valve module 5 and the oxidant gas circuit valve module 6 are opened according to the instruction, and when the fuel tank 7, the oxidant tank 8 and the pressurized gas management module 1 are kept in communication, the track control engine 9 ignites in the constant pressure mode until the track change is completed.

[0043] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "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 application and simplifying the description, and do not indicate or imply that the referred device or element 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 application.

[0044] The above describes the specific embodiments of the present invention. It should be understood that the present invention 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 essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A spacecraft propulsion system, It is characterized in that It comprises a pressurized gas management module (1), a fuel tank (7), an oxidizer tank (8) and a track control engine (9); The pressurized gas management module (1) is connected to the inlets of the fuel tank (7) and the oxidant tank (8) respectively through the gas pressure reducing device (2); the track control engine (9) is connected to the outlets of the fuel tank (7) and the oxidant tank (8) respectively; a fuel gas path one-way flow management device (3) and a fuel gas path valve module (5) are arranged in sequence between the gas pressure reducing device (2) and the fuel tank (7); an oxidant gas path one-way flow management device (4) and an oxidant gas path valve module (6) are arranged in sequence in the pipeline between the gas pressure reducing device (2) and the oxidant tank (8); a first pressure sensor (101) is arranged at the outlet of the gas pressure reducing device (2); a second pressure sensor (102) is arranged at the outlet of the oxidant tank (8); a third pressure sensor (103) is arranged at the outlet of the fuel tank (7); and a fourth pressure sensor (104) and a fifth pressure sensor (105) are arranged at the oxidant inlet and the fuel inlet of the track control engine (9); When the static pressure value of any one of the second pressure sensor (102) and the third pressure sensor (103) is greater than the static pressure value of the first pressure sensor (101), the rail control engine (9) is first started and ignited in a pressure drop mode, and then switched from the pressure drop mode to a constant pressure mode. The so-called pressure drop mode means that when the rail control engine (9) is ignited and started, the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) are in a closed state, and the fuel tank (7) and the oxidant tank (8) are not connected to the gas circuit booster module, and the rail control engine (9) is started and ignited.

2. The spacecraft propulsion system according to claim 1, It is characterized in that The track control engine (9) switches the propulsion system working mode from the pressure drop mode to the constant pressure mode by means of an autonomous management program or a delayed instruction.

3. The spacecraft propulsion system according to claim 2, It is characterized in that The method of using the autonomous management program is as follows: before the rail control engine (9) is ignited and started, the autonomous management program for high-operating-condition ignition of the rail control engine (9) is started through a ground injection command, the autonomous management program reads the pressure values ​​of the second pressure sensor (102), the third pressure sensor (103), the fourth pressure sensor (104), and the fifth pressure sensor (105), and when the autonomous management program determines that the pressure values ​​of at least three sensors among the second pressure sensor (102), the third pressure sensor (103), the fourth pressure sensor (104), and the fifth pressure sensor (105) are less than or equal to a set pressure threshold, the autonomous management program controls the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) to be opened.

4. The spacecraft propulsion system according to claim 2, It is characterized in that The method of using the delay command is as follows: before the rail control engine (9) is ignited and started, a delay command is injected on the ground, and the delay command is used to instruct the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) to open after a predetermined time after the rail control engine (9) is ignited and started in a pressure drop manner.

5. A method for starting a spacecraft propulsion system under high operating conditions, It is characterized in that The spacecraft propulsion system according to any one of claims 1 to 4 comprises the following steps: S1, judging the high operating state of the propulsion system: before the spacecraft changes its orbit, the propulsion system pressure is remotely measured and judged by the ground, and when the static pressure value of the first pressure sensor (101) is less than the static pressure value of the second pressure sensor (102) or the static pressure value of the first pressure sensor (101) is less than the static pressure value of the third pressure sensor (103), it is judged that the propulsion system is in a high operating state; S2, determining the high-operating-condition start-up condition of the rail control engine: performing remote sensing and judgment on the fourth pressure sensor (104) and the fifth pressure sensor (105) on the ground to determine that the static pressure value of the fourth pressure sensor (104) or the fifth pressure sensor (105) does not exceed the preset pressure value of the rail control engine (9); S3, the rail control engine starts ignition in a pressure drop mode: after step S1 and step S2, the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) close the valves according to the instruction, and in a state where the fuel tank (7), the oxidant tank (8) and the pressurized gas management module (1) are isolated, the rail control engine (9) starts ignition in a pressure drop mode; S4, switching of the ignition mode of the track control engine: after step S3, along with the ignition start of the track control engine (9), the ignition mode of the track control engine (9) is switched from the drop pressure mode to the constant pressure mode by using an autonomous management program or a delayed instruction; S5, ignition operation of the track control engine in constant pressure mode: after step S4, when the ignition mode of the track control engine (9) is switched from the pressure drop mode to the constant pressure mode, the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) are opened according to the instruction, and the fuel tank (7), the oxidant tank (8) and the boost gas management module (1) are kept in a connected state, and the track control engine (9) ignites in the constant pressure mode until the track change is completed.

6. The method for starting a spacecraft propulsion system at a high operating condition according to claim 5, It is characterized in that In the step S4, the autonomous management program is used in the following manner: before the rail control engine (9) is ignited and started, the autonomous management program for high-operating-condition ignition of the rail control engine (9) is started through a ground injection command, the autonomous management program reads the pressure values ​​of the second pressure sensor (102), the third pressure sensor (103), the fourth pressure sensor (104), and the fifth pressure sensor (105), and when the autonomous management program determines that the pressure values ​​of at least three sensors among the second pressure sensor (102), the third pressure sensor (103), the fourth pressure sensor (104), and the fifth pressure sensor (105) are less than or equal to a set pressure threshold, the autonomous management program controls the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) to be opened.

7. The method for starting a spacecraft propulsion system at a high operating condition according to claim 6, It is characterized in that The pressure threshold can be modified and adjusted in orbit according to ground remote control instructions.

8. The method for starting a spacecraft propulsion system at a high operating condition according to claim 6, It is characterized in that The pressure threshold of the second pressure sensor (102) is the difference between the locking pressure of the gas pressure reducing device (2) and the opening pressure of the oxidant gas path one-way flow management device (4); the pressure threshold of the third pressure sensor (103) is the difference between the locking pressure of the gas pressure reducing device (2) and the opening pressure of the fuel gas path one-way flow management device (3); the pressure threshold of the fourth pressure sensor (104) is the pressure value of the second pressure sensor (102) minus the flow resistance of the system pipeline between the oxidant tank (8) and the rail control engine (9); and the pressure threshold of the fifth pressure sensor (105) is the pressure value of the third pressure sensor (103) minus the flow resistance of the system pipeline between the fuel tank (7) and the rail control engine (9).

9. The method for starting a spacecraft propulsion system at a high operating condition according to claim 5, It is characterized in that In step S4, the delay instruction is used in the following manner: before the rail control engine (9) is ignited and started, a delay instruction is injected on the ground, and the delay instruction is used to instruct the fuel gas circuit valve module (5) and the oxidant gas circuit valve module (6) to open after a predetermined time after the rail control engine (9) is ignited and started in a pressure drop manner.

10. The method for starting a spacecraft propulsion system at a high operating condition according to claim 9, It is characterized in that The time set by the delay instruction retains a predetermined margin, ensuring that the pressure values ​​of the second pressure sensor (102) and the third pressure sensor (103) are lower than the pressure value of the first pressure sensor (101).

Images