Orbit control pipeline of spacecraft propulsion system and propellant supply control method thereof

Abstract

The present invention relates to a spacecraft propulsion system track control pipeline and a method for managing propellant thereof in the field of spacecraft propulsion technology, including an oxidizer tank, a fuel tank, a propulsion and control interactor, a track control engine, a valve, a heater, a temperature sensor, a pressure sensor, an oxidizer track control pipeline, a fuel track control pipeline and a controller. The present invention makes a judgment through the switch state of the propulsion track control pipeline valve. If a valve switch failure occurs, an on-orbit compensation measure is taken to ensure that the flow resistance of the oxidizer and fuel track control pipelines is consistent as much as possible, and the mixing ratio accuracy of the propulsion system track control engine due to the inconsistent switch state of the oxidizer and fuel pipeline valves is reduced, so that the remaining amount of propellant meets the design expectation, providing a guarantee for the spacecraft to achieve the on-orbit life.

Description

Technical Field

[0001] The present invention relates to the field of aerospace engine control technology, and in particular to a spacecraft propulsion system orbit control pipeline and a propellant supply control method thereof, and in particular to a method for judging the switch state of parallel valves in the spacecraft propulsion system orbit control pipeline and handling faults. Background Art

[0002] In recent years, with the continuous development of aerospace technology, high requirements have been put forward for the long-life on-orbit spacecraft. The life of a spacecraft is largely determined by the remaining amount of propellant, and the remaining amount of propellant is greatly affected by the mixing ratio of the propulsion system. The mixing ratio is the oxidizer consumption / fuel consumption. In the case of a large deviation in the mixing ratio, one propellant of the dual propulsion system will be exhausted in advance, resulting in an excessive surplus of the other propellant, which will cause the spacecraft to be unable to complete a long-life on-orbit mission. The mixing ratio of the propulsion system is mainly determined by the mixing ratio of the orbital control engine. Therefore, the propulsion system needs to ensure that the mixing ratio of the orbital control engine cannot have a large deviation. Generally, in order to ensure leakage after the orbital control engine is shut down, a valve will be added to the system orbital control pipeline, that is, upstream of the orbital control engine to achieve dual-channel redundancy of sealing. Considering that the orbital control pipeline can communicate reliably, two valves are usually set in parallel to manage the orbital control pipeline in parallel redundancy. However, since two valves are set in the oxidizer and fuel rail control lines, if at most one valve in each of the oxidizer and fuel lines cannot be opened and closed normally, it will have a great impact on the flow resistance of the rail control line, causing the pressure at the inlet of the rail control engine to deviate from the rated value, resulting in a large deviation in the mixing ratio of the rail control engine. Therefore, it is necessary to design a method to determine the opening and closing status of the rail control line valves on-orbit and provide an on-orbit compensation method for the resulting fault conditions.

[0003] Patent document CN112648110A (application number CN202011552380.1) discloses a solution for setting parallel valves upstream of a spacecraft orbit control engine to achieve a system design of double redundant sealing of engine valves + system valves. Patent document CN110989707A (application number: CN201911081695.X) discloses a method of using pipeline heating to achieve system pipeline pressure management. 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 orbit control pipeline and a propellant supply control method thereof.

[0005] According to the present invention, a spacecraft propulsion system orbit control pipeline includes an oxidizer tank, a fuel tank, a propulsion and control interactor, an orbit control engine, a valve, a heater, a temperature sensor, a pressure sensor, an oxidizer orbit control pipeline, a fuel orbit control pipeline and a controller;

[0006] The valve comprises a first valve, a second valve, a third valve and a fourth valve, the first valve, the second valve, the third valve and the fourth valve are electrically connected to the propulsion and control interactive device respectively, the propulsion and control interactive device is used to control the restart of the first valve, the second valve, the third valve and the fourth valve, the heater comprises a first heater and a second heater, the temperature sensor comprises an oxidant rail control pipeline temperature sensor and a second heater, and the pressure sensor comprises a first pressure sensor, a second pressure sensor, a third pressure sensor and a fourth pressure sensor;

[0007] The oxidant tank is in communication with the rail control engine through the oxidant rail control pipeline, the oxidant rail control pipeline is switched by the first valve and the second valve arranged in parallel, the fuel tank is in communication with the rail control engine through the fuel rail control pipeline, the fuel rail control pipeline is switched by the third valve and the fourth valve arranged in parallel, the first heater is attached to the oxidant rail control pipeline for heating, the second heater is attached to the fuel rail control pipeline for heating, the oxidant rail control pipeline temperature sensor is arranged on the oxidant rail control pipeline for detecting temperature, the fuel rail control pipeline temperature sensor is arranged on the fuel rail control pipeline for detecting temperature, the first pressure sensor is arranged at the outlet of the oxidant tank, the second pressure sensor is arranged at the oxidant inlet of the rail control engine, the third pressure sensor is arranged at the outlet of the fuel tank, and the fourth pressure sensor is arranged at the fuel inlet of the rail control engine;

[0008] The controller controls the first valve and the second valve on the oxidizer rail control pipeline and the third valve and the fourth valve on the fuel rail control pipeline to switch the first valve and the second valve on the oxidizer rail control pipeline according to the information about whether there is a faulty valve, so as to supply the propellant in a manner in which the number of valve switches on the oxidizer rail control pipeline and the fuel rail control pipeline is consistent.

[0009] The present invention also provides a method for controlling the supply of propellant for a spacecraft propulsion system, which uses the orbit control pipeline of the spacecraft propulsion system, and comprises the following steps:

[0010] S1, valve switch state detection: when the rail control pipeline is filled, by opening and closing the first valve and the second valve, and heating the first heater, it is detected whether there is a faulty valve that cannot be opened and closed normally between the first valve and the second valve, and the specific fault is determined; by opening and closing the third valve and the fourth valve, and heating the second heater, it is detected whether there is a faulty valve that cannot be opened and closed normally between the third valve and the fourth valve, and the specific fault is determined; if there is a faulty valve, step S2 is entered, and if there is no faulty valve, step S3 is directly entered;

[0011] S2, faulty valve processing: after step S1, the controller sends an instruction to reset the faulty valve, and then re-detects and judges through step S1. If the fault of the faulty valve still cannot be eliminated, the propulsion and control interactive device is restarted, and then the controller continues to send instructions to reset the faulty valve, and re-detects and judges through step S1 again, and then enters step S3 in the state that the fault is eliminated or the fault still exists;

[0012] S3, propellant supply control: the controller controls the first valve and the second valve on the oxidizer rail control pipeline and the third valve and the fourth valve on the fuel rail control pipeline according to the information of whether there is a faulty valve, so as to supply the propellant in a manner that the number of valves opened and closed on the oxidizer rail control pipeline and the fuel rail control pipeline are consistent.

[0013] In some embodiments, in step S1, the operation steps for determining whether the opening state and the closing state of the first valve and the second valve are both intact are: firstly, the first valve is opened, and the pressure values ​​of the first pressure sensor and the second pressure sensor are the same; then, the second valve is opened and the first valve is closed; the oxidant rail control pipeline is heated to a set value by the first heater; during the heating process, the pressure values ​​of the second pressure sensor and the first pressure sensor are kept consistent; then, the second valve and the first heater are closed, and the pressure value of the second pressure sensor gradually decreases to a predetermined value;

[0014] In some embodiments, in step S1, the operation steps for determining whether the open state and the closed state of the third valve and the fourth valve are both intact are: first, the third valve is opened, and the pressure values ​​of the third pressure sensor and the fourth pressure sensor are the same; then, the fourth valve is opened and the third valve is closed; the fuel rail control pipeline is heated to a set value by the second heater; during the heating process, the pressure values ​​of the fourth pressure sensor and the third pressure sensor are kept consistent; then, the fourth valve and the second heater are closed, and the pressure value of the fourth pressure sensor gradually decreases to a predetermined value.

[0015] In some embodiments, in step S1, the operation steps for determining that the first valve cannot be opened normally and the second valve can be opened and closed normally are: firstly, the first valve is opened, and the pressure value of the second pressure sensor does not change; then, the second valve is opened, and the pressure value of the second pressure sensor becomes the same as the pressure value of the first pressure sensor; then, the first valve is closed, and the oxidant rail control pipeline is heated to a set value by the first heater. During the heating process, the pressure value of the second pressure sensor is kept consistent with that of the first pressure sensor; finally, the second valve and the first heater are closed, and the pressure value of the second pressure sensor slowly decreases to a predetermined value;

[0016] In some embodiments, in step S1, the operation steps of determining that the third valve cannot be opened normally and the fourth valve can be opened and closed normally are: firstly, the third valve is opened, and the pressure value of the third pressure sensor does not change; then, the fourth valve is opened, and the pressure value of the fourth pressure sensor becomes the same as the pressure value of the third pressure sensor; then, the third valve is closed, and the fuel rail control pipeline is heated to a set value by the second heater. During the heating process, the pressure value of the fourth pressure sensor is kept consistent with that of the third pressure sensor; finally, the fourth valve and the second heater are closed, and the pressure value of the fourth pressure sensor slowly decreases to a predetermined value;

[0017] In some embodiments, in step S1, the operating steps for determining that the second valve cannot be opened normally and the first valve can be opened and closed normally are: opening the first valve, the pressure value of the first pressure sensor is the same as that of the second pressure sensor, then opening the second valve and closing the first valve, heating the oxidant rail control pipeline to a set value through the first heater, the pressure value of the second pressure sensor increases rapidly during the heating process, and then immediately opening the first valve, and the pressure value of the second pressure sensor drops to the same as that of the first pressure sensor.

[0018] In some embodiments, in step S1, the operation steps of determining that the fourth valve cannot be opened normally and the third valve can be opened and closed normally are: opening the third valve, the pressure value of the third pressure sensor is the same as that of the fourth pressure sensor, then opening the fourth valve and closing the third valve, heating the fuel rail control pipeline to a set value through the second heater, the pressure value of the fourth pressure sensor increases rapidly during the heating process, and then immediately opening the third valve, and the pressure value of the fourth pressure sensor drops to the same as that of the third pressure sensor.

[0019] In some embodiments, in step S1, the operation steps of determining that one of the first valve and the second valve cannot be closed normally are: opening the first valve, the pressure value of the first pressure sensor is the same as that of the second pressure sensor, then opening the second valve and closing the first valve, heating the oxidant rail control pipeline to a set value by the first heater, during the heating process, the pressure value of the second pressure sensor is kept consistent with that of the first pressure sensor, and then closing the second valve, the second pressure sensor is kept at the same pressure value as that of the first pressure sensor;

[0020] In some embodiments, in step S1, the operation steps of determining that one of the third valve and the fourth valve cannot be closed normally are: opening the third valve, the pressure value of the third pressure sensor is the same as that of the fourth pressure sensor, then opening the fourth valve and closing the third valve, heating the fuel rail control pipeline to a set value through the second heater, during the heating process, the pressure value of the fourth pressure sensor is kept consistent with that of the third pressure sensor, and then closing the fourth valve, and the pressure value of the fourth pressure sensor is kept the same as that of the third pressure sensor.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] The present invention makes judgment through the switch state of the valve of the propulsion track control pipeline. If a valve switch failure occurs, on-orbit compensation measures are taken to ensure that the flow resistance of the oxidizer and fuel track control pipelines is consistent as much as possible, thereby reducing the impact of inconsistent switch states of the oxidizer and fuel pipeline valves on the mixing ratio accuracy of the propulsion system track control engine, so that the remaining propellant meets the design expectations, providing a guarantee for the spacecraft to achieve its on-orbit life. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] 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:

[0024] Figure 1 This is a schematic diagram of the orbit control pipeline system of the spacecraft propulsion system of the present invention;

[0025] Figure 2 It is a flow chart of the propellant supply control method of the spacecraft propulsion system. 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 orbit control pipeline, such as Figure 1 As shown, it includes an oxidant tank 1, a fuel tank 2, a propulsion and control interactor 3, a track control engine 4, a valve 5, a heater 6, a temperature sensor 7, a pressure sensor 8, an oxidant track control pipeline, a fuel track control pipeline and a controller 11. The valve 5 includes a first valve 51, a second valve 52, a third valve 53 and a fourth valve 54. The first valve 51, the second valve 52, the third valve 53 and the fourth valve 54 are electrically connected to the propulsion and control interactor 3 respectively, and the propulsion and control interactor 3 is used to control the restart of the first valve 51, the second valve 52, the third valve 53 and the fourth valve 54. The heater 6 includes a first heater 61 and a second heater 62. The temperature sensor 7 includes an oxidant track control pipeline temperature sensor 71 and a second heater 72. The pressure sensor 8 includes a first pressure sensor 81, a second pressure sensor 82, a third pressure sensor 83 and a fourth pressure sensor 84.

[0029] The oxidizer tank 1 is connected to the track control engine 4 through the oxidizer track control pipeline. The pipeline of the oxidizer track control pipeline is controlled by the first valve 51 and the second valve 52 arranged in parallel. A first pressure sensor 81 is installed at the propellant outlet of the oxidizer tank 1. A second pressure sensor 82 is installed at the propellant inlet of the oxidizer track control pipeline close to the track control engine 4. The first heater 61 is attached to the outer peripheral surface of the oxidizer track control pipeline for heating it. The first temperature sensor 71 is connected to the oxidizer track control pipeline for detecting its temperature after heating.

[0030] The fuel tank 2 is connected to the rail control engine 4 through the fuel rail control pipeline. The pipeline of the fuel rail control pipeline is controlled by the third valve 53 and the fourth valve 54 arranged in parallel. A third pressure sensor 83 is installed at the propellant outlet of the fuel tank 2. A fourth pressure sensor 84 is installed at the propellant inlet of the fuel rail control pipeline close to the rail control engine 4. The second heater 62 is attached to the position surface of the fuel rail control pipeline for heating it. The second temperature sensor 72 is connected to the fuel rail control pipeline for detecting the temperature after heating.

[0031] The controller 11 controls the opening and closing of the first valve 51 and the second valve 52 on the oxidizer rail control pipeline and the third valve 53 and the fourth valve 54 on the fuel rail control pipeline according to the information of whether there is a faulty valve, and supplies the propellant in a manner that the number of valve openings on the oxidizer rail control pipeline and the fuel rail control pipeline is consistent, so as to ensure that the flow resistance of the oxidizer and fuel pipelines is as balanced as possible, and the track is changed. The method for judging the fault of the first valve 51, the second valve 52, the third valve 53 and the fourth valve 54 is mainly to judge the correctness of the valve opening and closing according to the pressure change in the pipeline by opening and closing the valve when the rail control pipeline is filled, and heating the oxidizer rail control pipeline and the fuel rail control pipeline respectively.

[0032] The switch states of two sets of valves arranged in parallel on the oxidizer rail control pipeline and the fuel rail control pipeline are detected, and the valve working conditions are determined to be three situations through detection. Take the first valve 51 and the second valve 52 on the oxidizer rail control pipeline as an example: the first working condition is that the opening and closing states of the first valve 51 and the second valve 52 are both in normal state; the second working condition is that one of the first valve 51 and the second valve 52 cannot be opened normally; the third working condition is that one of the first valve 51 and the second valve 52 cannot be closed normally. Correspondingly, the third valve 53 and the fourth valve 54 on the fuel rail control pipeline are also in the above three working conditions. The second working condition and the third working condition are both fault working conditions, and the fault working condition means that at most only one valve in any pipeline of the oxidizer rail control pipeline and the fuel rail control pipeline is faulty.

[0033] The detection and judgment method of the first working condition is:

[0034] For the oxidant rail control pipeline, the operating steps for judging whether the opening state and the closing state of the first valve 51 and the second valve 52 are normal are as follows: when the rail control pipeline is filled, first open the first valve 51, the pressure values ​​of the first pressure sensor 81 and the second pressure sensor 82 are the same, then open the second valve 52 and close the first valve 51, heat the oxidant rail control pipeline to the set value through the first heater 61, during the heating process, the pressure value of the second pressure sensor 82 is consistent with that of the first pressure sensor 81, then close the second valve 52 and the first heater 61, and the pressure value of the second pressure sensor 82 gradually decreases to the predetermined value.

[0035] For the fuel rail control pipeline, the operating steps for judging whether the opening state and the closing state of the third valve 53 and the fourth valve 54 are normal are as follows: when the rail control pipeline is filled, the third valve 53 is first opened, and the pressure values ​​of the third pressure sensor 83 and the fourth pressure sensor 84 are the same; then the fourth valve 54 is opened and the third valve 53 is closed, and the fuel rail control pipeline is heated to a set value by the second heater 62. During the heating process, the pressure values ​​of the fourth pressure sensor 84 and the third pressure sensor 83 are kept consistent; then the fourth valve 54 and the second heater 62 are closed, and the pressure value of the fourth pressure sensor 84 gradually decreases to a predetermined value.

[0036] The detection and judgment method of the second working condition is:

[0037] For the oxidant rail control pipeline, the operating steps for determining that the first valve 51 cannot be opened normally and the second valve 52 can be opened and closed normally are: first open the first valve 51, and the pressure value of the second pressure sensor 82 does not change; then open the second valve 52, and the pressure value of the second pressure sensor 82 becomes the same as the pressure value of the first pressure sensor 81; then close the first valve 51, and heat the oxidant rail control pipeline to the set value through the first heater 61. During the heating process, the pressure values ​​of the second pressure sensor 82 and the first pressure sensor 81 remain consistent; finally, close the second valve 52 and the first heater 6, and the pressure value of the second pressure sensor 82 slowly drops to a predetermined value.

[0038] The operating steps for determining that the second valve 52 cannot be opened normally and the first valve 51 can be opened and closed normally are: open the first valve 51, the pressure value of the first pressure sensor 81 is the same as that of the second pressure sensor 82, then open the second valve 52 and close the first valve 51, heat the oxidant rail control pipeline to the set value through the first heater 61, and the pressure value of the second pressure sensor 82 increases rapidly during the heating process, and then immediately open the first valve 51, and the pressure value of the second pressure sensor 82 drops to the same as that of the first pressure sensor 81.

[0039] For the fuel rail control pipeline, the operation steps for determining that the third valve 53 cannot be opened normally and the fourth valve 54 can be opened and closed normally are: first, the third valve 53 is opened, and the pressure value of the third pressure sensor 83 does not change; then, the fourth valve 54 is opened, and the pressure value of the fourth pressure sensor 84 becomes the same as the pressure value of the third pressure sensor 83; then, the third valve 53 is closed, and the fuel rail control pipeline is heated to a set value by the second heater 62. During the heating process, the pressure values ​​of the fourth pressure sensor 84 and the third pressure sensor 83 are kept consistent; finally, the fourth valve 54 and the second heater 62 are closed, and the pressure value of the fourth pressure sensor 84 slowly decreases to a predetermined value.

[0040] The operation steps for determining that the fourth valve 54 cannot be opened normally and the third valve 53 can be opened and closed normally are: open the third valve 53, the pressure value of the third pressure sensor 83 is the same as that of the fourth pressure sensor 84, then open the fourth valve 54 and close the third valve 53, heat the fuel rail control pipeline to a set value through the second heater 62, the pressure value of the fourth pressure sensor 84 increases rapidly during the heating process, and then immediately open the third valve 53, and the pressure value of the fourth pressure sensor 84 drops to the same as that of the third pressure sensor 83.

[0041] The determination method for the third working condition is:

[0042] For the oxidant rail control pipeline, the operating steps for determining that one of the first valve 51 and the second valve 52 cannot be closed normally are: open the first valve 51, the pressure values ​​of the first pressure sensor 81 and the second pressure sensor 82 are the same, then open the second valve 52 and close the first valve 51, heat the oxidant rail control pipeline to the set value through the first heater 61, the pressure values ​​of the second pressure sensor 82 and the first pressure sensor 81 are consistent during the heating process, and then close the second valve 52, and the second pressure sensor 82 maintains the same pressure value as the first pressure sensor 81.

[0043] For the fuel rail control pipeline, the operation steps for determining that one of the third valve 53 and the fourth valve 54 cannot be closed normally are: open the third valve 53, the pressure value of the third pressure sensor 83 is the same as that of the fourth pressure sensor 84, then open the fourth valve 54 and close the third valve 53, heat the fuel rail control pipeline to a set value through the second heater 62, during the heating process, the pressure value of the fourth pressure sensor 84 is consistent with that of the third pressure sensor 83, and then close the fourth valve 54, and the fourth pressure sensor 84 maintains the same pressure value as that of the third pressure sensor 83.

[0044] Example 2

[0045] This embodiment 2 provides a propellant supply control method for a spacecraft propulsion system orbit control engine, which is formed by using the orbit control pipeline of the spacecraft propulsion system in embodiment 1. Figure 2 As shown, the valve switch state judgment and fault handling method involved in this embodiment is performed according to the flow chart. At the same time, it is explained that in order to simplify the text in the drawings, valve 1 in the drawings represents the first valve 51, valve 2 represents the second valve 52, valve 3 represents the third valve 53, and valve 4 represents the fourth valve 54. It includes the following steps:

[0046] S1, valve switch state detection: when the rail control pipeline is filled, by opening and closing the first valve 51 and the second valve 52, and heating the first heater 61, it is detected whether there is a faulty valve that cannot be opened and closed normally in the first valve 51 and the second valve 52, and the specific fault is determined. By opening and closing the third valve 53 and the fourth valve 54, and heating the second heater 62, it is detected whether there is a faulty valve that cannot be opened and closed normally in the third valve 53 and the fourth valve 54, and the specific fault is determined. If there is a faulty valve, it goes to step S2, and if there is no faulty valve, it goes directly to step S3. The detection and judgment of the opening and closing states of the first valve 51 and the second valve 52 located on the oxidant rail control pipeline 9 and the third valve 53 and the fourth valve 54 located on the fuel rail control pipeline 10 adopt the detection and judgment method in Example 1, which will not be repeated here.

[0047] S2, faulty valve processing: after step S1, the controller 11 sends instructions to reset the faulty valve, and then re-detects and judges through step S1. If the fault of the faulty valve still cannot be eliminated, restart the propulsion and control interactive device 3, and then the controller 11 continues to send instructions to reset the faulty valve, and re-detects and judges through step S1 again, and then enters step S3 when the fault is eliminated or the fault still exists.

[0048] S3, propellant supply control: the controller 11 controls the opening and closing of the first valve 51 and the second valve 52 on the oxidizer rail control pipeline and the third valve 53 and the fourth valve 54 on the fuel rail control pipeline according to the information of whether there is a faulty valve, and controls the propellant supply in a manner that the opening and closing numbers of the valves on the oxidizer rail control pipeline and the fuel rail control pipeline are consistent.

[0049] There are several specific situations:

[0050] (1) If the first valve 51 or the second valve 52 cannot be opened, and the third valve 53 or the fourth valve 54 cannot be opened, the track change is performed while the second valve 52 or the first valve 51 , the fourth valve 54 or the third valve 53 is kept open.

[0051] (2) If the first valve 51 or the second valve 52 cannot be opened, and the third valve 53 and the fourth valve 54 are both normal, the track change is performed while keeping valve 2 or the first valve 1 open and one of the third valve 53 and the fourth valve 54 open.

[0052] (3) If the first valve 51 or the second valve 52 cannot be opened and one of the third valve 53 and the fourth valve 54 cannot be closed, the track change is performed while keeping the second valve 52 or the first valve 1 open and one of the third valve 53 and the fourth valve 54 open.

[0053] (4) If the first valve 51 and the second valve 52 are both normal and the third valve 53 or the fourth valve 54 cannot be opened, the track change is performed with one of the first valve 51 and the second valve 52 open and the fourth valve 55 or the third valve 53 open.

[0054] (5) One of the first valve 51 and the second valve 52 cannot be closed, and the third valve 53 or the fourth valve 54 cannot be opened: the track change is performed while keeping one of the first valve 51 and the second valve 52 open and the fourth valve 55 or the third valve 53 open.

[0055] (6) If one of the first valve 51 and the second valve 52 cannot be closed, and the third valve 53 and the fourth valve 54 are normal, the track change is performed while keeping all four valves in the open state.

[0056] (7) If the first valve 51 and the second valve 52 are normal and one of the third valve 53 and the fourth valve 54 cannot be closed, the track change is performed while keeping all four valves open at the same time.

[0057] The technical solution provided in this embodiment is a method for judging the switch state of parallel valves and handling faults. The method mainly detects the normal working condition and the faulty working condition by comprehensive methods of valve switch, pipeline heating, and pressure parameter changes. For the faulty working condition, on-orbit compensation is carried out. After taking compensation measures, the mixing ratio accuracy of the orbital control engine is guaranteed to be unaffected as much as possible, and the difference in flow resistance of the orbital control pipeline caused by the inconsistent switch state of the valves of the oxidizer and fuel orbital control pipelines of the spacecraft propulsion system is overcome, which further leads to the deviation of the mixing ratio of the orbital control engine, and finally affects the on-orbit life of the spacecraft, providing a guarantee for the long-term on-orbit life of the spacecraft.

[0058] The method for judging the switch status of valves described in the present invention has undergone corresponding flight experiments. In subsequent flight applications, it can be combined with the judgment of fault conditions and the method of handling faults on-orbit to ensure that the number of switch valves in the oxidizer and fuel pipelines is consistent, and the flow resistance of the oxidizer and fuel rail control pipelines is consistent as much as possible, further ensuring the mixing ratio accuracy of the propulsion system's rail control engine, so that the remaining propellant meets the design expectations, providing a guarantee for the spacecraft to achieve its on-orbit life.

[0059] 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.

[0060] 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 orbit control pipeline, It is characterized in that It includes an oxidizer tank (1), a fuel tank (2), a propulsion and control interactor (3), a track control engine (4), a valve (5), a heater (6), a temperature sensor (7), a pressure sensor (8), an oxidizer track control pipeline, a fuel track control pipeline and a controller (11); The valve (5) comprises a first valve (51), a second valve (52), a third valve (53) and a fourth valve (54), wherein the first valve (51), the second valve (52), the third valve (53) and the fourth valve (54) are electrically connected to the propulsion and control interactive device (3) respectively, and the propulsion and control interactive device (3) is used to control the restart of the first valve (51), the second valve (52), the third valve (53) and the fourth valve (54); the heater (6) comprises a first heater (61) and a second heater (62); the temperature sensor (7) comprises an oxidant rail control pipeline temperature sensor (71) and a fuel rail control pipeline temperature sensor (72); and the pressure sensor (8) comprises a first pressure sensor (81), a second pressure sensor (82), a third pressure sensor (83) and a fourth pressure sensor (84); The oxidant tank (1) is connected to the rail control engine (4) through the oxidant rail control pipeline, and the oxidant rail control pipeline is controlled by the first valve (51) and the second valve (52) arranged in parallel. The fuel tank (2) is connected to the rail control engine (4) through the fuel rail control pipeline, and the fuel rail control pipeline is controlled by the third valve (53) and the fourth valve (54) arranged in parallel. The first heater (61) is attached to the oxidant rail control pipeline for heating, and the second heater (62) is attached to the fuel rail control pipeline. The oxidant rail control pipeline is used for heating, the oxidant rail control pipeline temperature sensor (71) is arranged on the oxidant rail control pipeline for detecting temperature, the fuel rail control pipeline temperature sensor (72) is arranged on the fuel rail control pipeline for detecting temperature, the first pressure sensor (81) is arranged at the outlet of the oxidant tank (1), the second pressure sensor (82) is arranged at the oxidant inlet of the rail control engine (4), the third pressure sensor (83) is arranged at the outlet of the fuel tank (2), and the fourth pressure sensor (84) is arranged at the fuel inlet of the rail control engine (4); The controller (11) controls the first valve (51) and the second valve (52) on the oxidizer rail control pipeline and the third valve (53) and the fourth valve (54) on the fuel rail control pipeline according to the information on whether there is a faulty valve, so as to supply the propellant in a manner in which the number of valves on and off on the oxidizer rail control pipeline and the fuel rail control pipeline are consistent.

2. A method for controlling the supply of propellant to a spacecraft propulsion system, It is characterized in that The spacecraft propulsion system orbit control pipeline according to claim 1 comprises the following steps: S1, valve switch state detection: when the rail control pipeline is filled, by opening and closing the first valve (51) and the second valve (52), and heating the first heater (61), it is detected whether there is a faulty valve that cannot be opened and closed normally between the first valve (51) and the second valve (52), and the specific fault is determined; by opening and closing the third valve (53) and the fourth valve (54), and heating the second heater (62), it is detected whether there is a faulty valve that cannot be opened and closed normally between the third valve (53) and the fourth valve (54), and the specific fault is determined; if there is a faulty valve, the process proceeds to step S2; if there is no faulty valve, the process directly proceeds to step S3; S2, faulty valve processing: after step S1, the controller (11) sends an instruction to reset the faulty valve, and then re-detects and judges through step S1. If the fault of the faulty valve still cannot be eliminated, the propulsion and control interactive device (3) is restarted, and then the controller (11) continues to send an instruction to reset the faulty valve, and re-detects and judges through step S1 again, and then enters step S3 in the state that the fault is eliminated or the fault still exists; S3, propellant supply control: the controller (11) controls the first valve (51) and the second valve (52) on the oxidizer rail control pipeline and the third valve (53) and the fourth valve (54) on the fuel rail control pipeline according to the information of whether there is a faulty valve, so as to supply the propellant in a manner that the number of valves on and off on the oxidizer rail control pipeline and the fuel rail control pipeline are consistent.

3. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for judging whether the opening state and the closing state of the first valve (51) and the second valve (52) are intact are as follows: firstly, the first valve (51) is opened, and the pressure values ​​of the first pressure sensor (81) and the second pressure sensor (82) are the same; then, the second valve (52) is opened and the first valve (51) is closed; the oxidant rail control pipeline is heated to a set value by the first heater (61); during the heating process, the pressure values ​​of the second pressure sensor (82) and the first pressure sensor (81) are kept consistent; then, the second valve (52) and the first heater (61) are closed, and the pressure value of the second pressure sensor (82) gradually decreases to a predetermined value.

4. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for judging whether the open state and the closed state of the third valve (53) and the fourth valve (54) are both intact are as follows: firstly, the third valve (53) is opened, and the pressure values ​​of the third pressure sensor (83) and the fourth pressure sensor (84) are the same; then, the fourth valve (54) is opened and the third valve (53) is closed, and the fuel rail control pipeline is heated to a set value by the second heater (62). During the heating process, the pressure values ​​of the fourth pressure sensor (84) and the third pressure sensor (83) are kept consistent; then, the fourth valve (54) and the second heater (62) are closed, and the pressure value of the fourth pressure sensor (84) gradually decreases to a predetermined value.

5. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for determining that the first valve (51) cannot be opened normally and the second valve (52) can be opened and closed normally are: firstly, the first valve (51) is opened, and the pressure value of the second pressure sensor (82) does not change; then, the second valve (52) is opened, and the pressure value of the second pressure sensor (82) becomes the same as the pressure value of the first pressure sensor (81); then, the first valve (51) is closed, and the oxidant rail control pipeline is heated to a set value by the first heater (61); during the heating process, the pressure value of the second pressure sensor (82) is kept consistent with that of the first pressure sensor (81); finally, the second valve (52) and the first heater (61) are closed, and the pressure value of the second pressure sensor (82) slowly decreases to a predetermined value.

6. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for determining that the third valve (53) cannot be opened normally and the fourth valve (54) can be opened and closed normally are: firstly, the third valve (53) is opened, and the pressure value of the third pressure sensor (83) does not change; then, the fourth valve (54) is opened, and the pressure value of the fourth pressure sensor (84) becomes the same as the pressure value of the third pressure sensor (83); then, the third valve (53) is closed, and the fuel rail control pipeline is heated to a set value by the second heater (62); during the heating process, the pressure value of the fourth pressure sensor (84) is kept consistent with that of the third pressure sensor (83); finally, the fourth valve (54) and the second heater (62) are closed, and the pressure value of the fourth pressure sensor (84) slowly decreases to a predetermined value.

7. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for determining that the second valve (52) cannot be opened normally and the first valve (51) can be opened and closed normally are: opening the first valve (51), the pressure value of the first pressure sensor (81) is the same as that of the second pressure sensor (82), then opening the second valve (52) and closing the first valve (51), heating the oxidant rail control pipeline to a set value through the first heater (61), the pressure value of the second pressure sensor (82) increases rapidly during the heating process, and then immediately opening the first valve (51), and the pressure value of the second pressure sensor (82) decreases to the same as that of the first pressure sensor (81).

8. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for determining that the fourth valve (54) cannot be opened normally and the third valve (53) can be opened and closed normally are: opening the third valve (53), the pressure value of the third pressure sensor (83) is the same as that of the fourth pressure sensor (84), then opening the fourth valve (54) and closing the third valve (53), heating the fuel rail control pipeline to a set value through the second heater (62), the pressure value of the fourth pressure sensor (84) increases rapidly during the heating process, and then immediately opening the third valve (53), the pressure value of the fourth pressure sensor (84) decreases to the same as that of the third pressure sensor (83).

9. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for determining that one of the first valve (51) and the second valve (52) cannot be closed normally are: opening the first valve (51), the pressure values ​​of the first pressure sensor (81) and the second pressure sensor (82) are the same, then opening the second valve (52) and closing the first valve (51), heating the oxidant rail control pipeline to a set value through the first heater (61), during the heating process, the pressure values ​​of the second pressure sensor (82) and the first pressure sensor (81) are kept consistent, and then closing the second valve (52), the second pressure sensor (82) is kept at the same pressure value as the first pressure sensor (81).

10. The method for controlling the supply of propellant to a spacecraft propulsion system according to claim 2, It is characterized in that In step S1, the operation steps for determining that one of the third valve (53) and the fourth valve (54) cannot be closed normally are: opening the third valve (53), the pressure value of the third pressure sensor (83) is the same as that of the fourth pressure sensor (84), then opening the fourth valve (54) and closing the third valve (53), heating the fuel rail control pipeline to a set value through the second heater (62), the pressure value of the fourth pressure sensor (84) is consistent with that of the third pressure sensor (83) during the heating process, and then closing the fourth valve (54), the pressure value of the fourth pressure sensor (84) is kept the same as that of the third pressure sensor (83).

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