A gas supply control method and device for an ion electric propulsion system

Abstract

This application relates to a gas supply control method and device for an ion electric propulsion system. Among them, the method includes: obtaining the failure condition of the ion thruster path and the xenon cylinder pressure information for the gas supply control of the ion electric propulsion system; formulating a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the failure condition of the ion thruster path; and adjusting the gas supply condition of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy. This application can adjust the gas supply condition of the gas supply control of the ion electric propulsion system. The synchronous / asynchronous autonomous switching strategy of this application realizes the optimal control objectives of gas supply accuracy, gas supply efficiency, and valve life. This application proposes a pressure compensation control scheme for the single-point failure of the heating wire of the thermal throttler, that is, the failure condition of the ion thruster path, so that the electric propulsion system in the worst case still has the necessary working ability.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft electric propulsion systems. More specifically, the present invention relates to a gas supply control method and device for an ion electric propulsion system. Background Art

[0002] In space science and technology, common space propulsion technologies include chemical propulsion technology and ion electric propulsion technology. Among them, ion electric propulsion technology has the characteristics of small thrust, high specific impulse, and high efficiency, and is widely used in spacecraft attitude control, position holding, orbital maneuvering, and interstellar flight. The principle of ion electric propulsion technology is to first ionize the gaseous working medium and accelerate the ions to be ejected under the action of a strong electric field, and use the reaction force generated by the ejection to push the satellite to move.

[0003] The gas supply control in the ion electric propulsion system determines the thrust of the ion thruster. At present, there is a need for a gas supply control method and device for an ion electric propulsion system in the prior art, which can adjust the gas supply situation of the ion electric propulsion system to ensure gas supply accuracy and gas supply efficiency, etc. Summary of the Invention

[0004] The embodiments of the present application provide a gas supply control method and device for an ion electric propulsion system. To have a basic understanding of some aspects of the disclosed embodiments, a simple summary is given below. This summary part is not a general review, nor is it to identify key / important constituent elements or depict the protection scope of these embodiments. Its sole purpose is to present some concepts in a simple form as a preface to the subsequent detailed description.

[0005] In a first aspect, the present application provides a gas supply control method for an ion electric propulsion system, and the method includes:

[0006] Obtain the failure situation of the ion thruster path and the xenon cylinder pressure information for the gas supply control of the ion electric propulsion system;

[0007] According to the failure situation of the ion thruster path, formulate a pressure compensation control scheme for the gas supply control of the ion electric propulsion system;

[0008] According to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy, adjust the gas supply situation of the gas supply control of the ion electric propulsion system.

[0009] According to a preferred implementation manner, the obtaining of the failure situation of the ion thruster path for the gas supply control of the ion electric propulsion system includes:

[0010] Obtain the failure of the neutralizer path, the main cathode path, or the anode path for the gas supply control of the ion electric propulsion system;

[0011] Taking the failure of the neutralizer passage, the failure of the main cathode passage, or the failure of the anode passage as the ion thruster passage failure situation for the gas supply control of the ion electric propulsion system.

[0012] According to a preferred embodiment, the cathode passage and the anode passage are controlled separately. The cathode passage includes the neutralizer passage corresponding to the failure of the neutralizer passage and the main cathode passage corresponding to the failure of the main cathode passage; the anode passage failure corresponds to the anode passage.

[0013] According to a preferred embodiment, formulating the pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the ion thruster passage failure situation includes:

[0014] When the neutralizer passage fails, the formulated pressure compensation control scheme is not to take treatment measures in orbit;

[0015] When the main cathode passage fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer passage and the temperature control of the anode thermal throttle corresponding to the anode passage;

[0016] When the anode passage fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer passage and the temperature control of the main cathode thermal throttle corresponding to the main cathode passage.

[0017] According to a preferred embodiment, adjusting the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy includes:

[0018] The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or the asynchronous control mode of the gas supply control of the ion electric propulsion system;

[0019] When the xenon gas cylinder pressure information meets the preset pressure information, adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous control mode;

[0020] When the xenon gas cylinder pressure information does not meet the preset pressure information, adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the asynchronous control mode.

[0021] In a second aspect, the present application provides an ion electric propulsion system gas supply control device, and the device includes:

[0022] An acquisition module, configured to acquire the failure condition of the ion thruster path and the xenon gas cylinder pressure information for the gas supply control of the ion electric propulsion system;

[0023] A scheme formulation module, configured to formulate a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the failure condition of the ion thruster path;

[0024] An adjustment module, configured to adjust the gas supply condition of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy.

[0025] According to a preferred embodiment, the acquisition module is specifically configured to:

[0026] Acquire the failure of the neutralizer path, the main cathode path, or the anode path in the gas supply control of the ion electric propulsion system;

[0027] Use the failure of the neutralizer path, the main cathode path, or the anode path as the failure condition of the ion thruster path in the gas supply control of the ion electric propulsion system.

[0028] According to a preferred embodiment, the cathode path and the anode path are controlled separately. The cathode path includes the neutralizer path corresponding to the failure of the neutralizer path and the main cathode path corresponding to the failure of the main cathode path; the failure of the anode path corresponds to the anode path.

[0029] According to a preferred embodiment, the scheme formulation module is specifically configured to:

[0030] When the neutralizer path fails, the formulated pressure compensation control scheme is not to take any treatment measures in orbit;

[0031] When the main cathode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the anode thermal throttle corresponding to the anode path;

[0032] When the anode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the main cathode thermal throttle corresponding to the main cathode path.

[0033] According to a preferred embodiment, the adjustment module is specifically configured to:

[0034] The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or the asynchronous control mode of the gas supply control of the ion electric propulsion system;

[0035] When the xenon gas cylinder pressure information meets the preset pressure information, adjust the gas supply condition of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous control method;

[0036] When the xenon gas cylinder pressure information does not meet the preset pressure information, adjust the gas supply condition of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the asynchronous control method.

[0037] In a third aspect, the present application provides a computer storage medium storing multiple instructions adapted to be loaded and executed by a processor to perform the above method steps.

[0038] In a fourth aspect, the present application provides a terminal, which may include: a processor and a memory; wherein, the memory stores a computer program adapted to be loaded and executed by the processor to perform the above method steps.

[0039] The technical solution provided by the present application may include the following beneficial effects:

[0040] In the present application, the gas supply control method for the ion electric propulsion system obtains the ion thruster path failure condition and the xenon gas cylinder pressure information of the gas supply control of the ion electric propulsion system; formulates a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the ion thruster path failure condition; and adjusts the gas supply condition of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous and asynchronous autonomous switching strategy. The present application can adjust the gas supply condition of the gas supply control of the ion electric propulsion system. The synchronous and asynchronous autonomous switching strategy of the present application realizes the optimal control objectives of gas supply accuracy, gas supply efficiency, and valve life; the present application proposes a pressure compensation control scheme for the single-point failure of the heating wire of the thermal throttler, that is, the ion thruster path failure condition, so that the electric propulsion system in the worst case still has the necessary working ability. In addition, the present application regards the neutralizer path failure, the main cathode path failure, or the anode path failure as the ion thruster path failure condition of the gas supply control of the ion electric propulsion system; the cathode path and the anode path are controlled separately. The cathode path includes the neutralizer path corresponding to the neutralizer path failure and the main cathode path corresponding to the main cathode path failure; the anode path failure corresponds to the anode path; from the perspective of hardware configuration, the cathode path and the anode path are controlled separately. Since the ion thruster requires the neutralizer to arc before the anode, the gas supply of the anode path must be closed during the ignition process of the neutralizer, which can optimize the gas supply timing on the premise of ensuring the normal operation of the ion electric propulsion system and achieve the purpose of saving xenon gas.

[0041] It should be understood that the above general description and the following detailed description are merely exemplary and explanatory, and do not limit the present invention. Brief Description of the Drawings

[0042] The drawings herein are incorporated into and constitute a part of this specification, showing embodiments consistent with the present invention, and are used together with the specification to explain the principles of the present invention.

[0043] Figure 1 is a schematic flowchart of a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application;

[0044] Figure 2 is a schematic diagram of the composition of a storage and supply subsystem of a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application;

[0045] Figure 3 is a synchronous and asynchronous control block diagram of a pressure regulating module of a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application;

[0046] Figure 4 is a schematic diagram of a neutralizer flow rate - temperature and pressure curve of a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application;

[0047] Figure 5 is a schematic diagram of a main cathode flow rate - temperature and pressure curve of a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application;

[0048] Figure 6 is a schematic diagram of an anode flow rate - temperature and pressure curve of a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application;

[0049] Figure 7 is a schematic diagram of a gas supply control device for an ion electric propulsion system provided by an embodiment of the present application;

[0050] Figure 8 is a schematic diagram of a terminal provided by an embodiment of the present application.

[0051] Reference Signs:

[0052] 10000, acquisition module, 20000, scheme formulation module, 30000, adjustment module;

[0053] 1001, processor, 1002, communication bus, 1003, user interface, 1004, network interface, 1005, memory. Detailed Embodiments

[0054] The following description and drawings fully illustrate specific embodiments of the present invention, enabling those skilled in the art to practice them.

[0055] It should be clear that the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0056] When the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. On the contrary, they are merely examples of systems and methods consistent with some aspects of the present invention as detailed in the appended claims.

[0057] In the description of the present invention, it should be understood that terms such as "first", "second", etc. are only used for descriptive purposes and cannot be construed as indicating or implying relative importance. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. In addition, in the description of the present invention, unless otherwise specified, "a plurality of" means two or more. "And / or" describes the association relationship of associated objects and indicates that three relationships can exist. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. The character " / " generally represents an "or" relationship between the associated objects before and after.

[0058] The following will be combined with the attached Figure 1 - attached Figure 6 , and a gas supply control method for an ion electric propulsion system provided by an embodiment of the present application will be introduced in detail.

[0059] Please refer to Figure 1-6 , the method of the embodiment of the present application may include the following steps:

[0060] A gas supply control method for an ion electric propulsion system provided by an embodiment of the present application, corresponding to the gas supply control system of the ion electric propulsion system. The gas supply control system is also called a storage and supply subsystem. As Figure 2As shown, the storage and supply subsystem is an important part of the ion electric propulsion system, generally consisting of a xenon gas cylinder, a pressure regulation module, and a flow regulation module. It realizes the precise flow supply of the neutralizer, main cathode, and anode of the ion thruster. The xenon gas cylinder generally only has temperature monitoring and is not the key point of control. Inside the xenon gas cylinder, xenon gas is filled into the cylinder through an inflation valve. Each path of the pressure regulation module consists of a pressure reducing valve and two solenoid valves, realizing the first-stage pressure reduction function from the high pressure of the xenon gas cylinder to the low pressure of the buffer gas cylinder. During the pressure regulation process, the pressure regulation module tests various values through a test port. The flow regulation module consists of a self-locking valve and a thermal throttle. The self-locking valve selects and closes the gas path flow direction through a switch, and the thermal throttle realizes the precise control of the three-way gas supply from the low pressure of the buffer gas cylinder to each ion thruster through temperature control. Three thermal throttles are required for the three-way gas supply, and different temperatures are used to finely adjust the three different flow rates. The gas supply control is to realize the three-way gas supply function that can meet the working timing requirements and working accuracy requirements of the ion thruster under normal working conditions, the entire life cycle, and the single-point failure of the heating wire of the thermal throttle. The thermal throttle is also called a thermal throttle valve, the flow regulation module is also called a flow regulation module, and the pressure regulation module is also called a pressure regulation module. The method will be described below in combination with the storage and supply subsystem.

[0061] Step S100, obtain the ion thruster path failure situation and xenon gas cylinder pressure information for the gas supply control of the ion electric propulsion system.

[0062] Among them, obtaining the ion thruster path failure situation for the gas supply control of the ion electric propulsion system includes:

[0063] Obtain the neutralizer path failure, main cathode path failure, or anode path failure in the gas supply control of the ion electric propulsion system; in the embodiments of the present application, the heating failure of the neutralizer thermal throttle will cause the neutralizer path failure, the heating failure of the main cathode thermal throttle will cause the main cathode path failure, and the heating failure of the anode thermal throttle will cause the anode path failure. The neutralizer path failure, the main cathode path failure, or the anode path failure is used as the ion thruster path failure situation in the gas supply control of the ion electric propulsion system.

[0064] In the present application, the cathode path and the anode path are controlled separately; the cathode path includes the neutralizer path corresponding to the neutralizer path failure and the main cathode path corresponding to the main cathode path failure. The cathode includes a neutralizer and a main cathode; the anode path failure corresponds to the anode path.

[0065] The gas supply timing control in the embodiments of this application is as follows: In terms of hardware configuration, the cathode path and the anode path are controlled separately. Since the ion thruster requires that the neutralizer must arc before the anode, and the anode gas supply accounts for 80% of the total gas volume; therefore, during the ignition process of the neutralizer, the gas supply to the anode path must be closed, which will neither increase the ignition time nor waste xenon gas. Generally, the ignition process of the neutralizer is between 240 s and 420 s. Taking a medium GEO satellite that works for 1.5 h each time as an example, this time accounts for about 4.5% - 7.8% of the on-orbit working time; calculated according to carrying 80 kg of propellant in 15 years and the anode gas supply accounting for 80%, at most 5.0 kg of xenon gas can be saved, and the only cost is to add 2 self-locking valves in the hardware. The weight of the 2 self-locking valves is about <100 g, and the weight reduction benefit is obvious.

[0066] As Figure 2 shown, the flow rate adjustment module consists of 6 self-locking valves to select the gas supply path. LV3 and LV4 ensure the path is unblocked, LV5 and LV6 ensure the neutralizer path and the main cathode path are unblocked, and LV7 and LV8 ensure the anode path is unblocked. The neutralizer path and the main cathode path are set separately, and the anode path is set separately to ensure that the anode gas supply can be controlled separately, providing hardware guarantee for saving xenon gas; in terms of control strategy, after the neutralizer ignites successfully, LV7 or LV8 is opened. Taking a medium GEO satellite in 15 years as an example, 5.0 kg of xenon gas can be saved.

[0067] Step S200, according to the failure situation of the ion thruster path, formulate a pressure compensation control scheme for the gas supply control of the ion electric propulsion system, including:

[0068] For the problem of single-point failure of the thermal throttle flow fine-tuning heating wire, different pressure compensation control schemes are formulated for different paths of the ion thruster to achieve compensation for different path failures, so that the electric propulsion system in the worst case still has the necessary working ability. Specifically, when the neutralizer path fails, the formulated pressure compensation control scheme is not to take any treatment measures in orbit; when the main cathode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the other two thermal throttles, that is, close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the anode thermal throttle corresponding to the anode path; when the anode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the other two thermal throttles, that is, close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the main cathode thermal throttle corresponding to the main cathode path.

[0069] In the embodiments of this application, the pressure compensation control scheme can also be called the optimal compensation strategy. Let P A represent the pressure of the buffer gas cylinder input at the inlet of the flow rate adjustment module after the cathode path fails. Let PMC represents the buffer gas cylinder pressure input at the inlet of the flow rate adjustment module after the anode path fails; P A and P MC can be obtained through ground calibration; it can also be determined by experience.

[0070] Figure 4 is the neutralizer flow rate - temperature, pressure curve; the abscissa is the temperature, the ordinate is the flow rate, and different curves represent different buffer gas cylinder pressures; the role of the flow rate adjustment module is to achieve a fixed flow rate. Therefore, when the temperature decreases after the temperature control ability fails, in order to keep the flow rate unchanged, the buffer gas cylinder pressure needs to be reduced; through Figure 4 it is obtained that for every 10°C decrease in the temperature of the neutralizer thermal throttle, the flow rate increases by an average of 1%, and a buffer gas cylinder pressure reduction of 0.008 Mpa is required for compensation; since the neutralizer flow rate has little impact on the thruster performance, the neutralizer thermal throttle temperature control failure is not processed in orbit. Figure 5 is the main cathode flow rate - temperature, pressure curve. For every 10°C decrease in the temperature of the main cathode thermal throttle, the flow rate increases by an average of 1%, and a buffer gas cylinder pressure reduction of 0.009 MPa is required for compensation. Figure 6 is the anode flow rate - temperature, pressure curve. For every 10°C decrease in the temperature of the anode thermal throttle, the flow rate increases by an average of 6.2%, and a buffer gas cylinder pressure reduction of 0.0063 MPa is required for compensation. The buffer gas cylinder pressure refers to the pressure inside the buffer gas cylinder.

[0071] Step S300, according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy, adjust the gas supply situation of the gas supply control of the ion electric propulsion system, including:

[0072] The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or the asynchronous control mode of the gas supply control of the ion electric propulsion system; when the xenon gas cylinder pressure information meets the preset pressure information, according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous control mode, adjust the gas supply situation of the gas supply control of the ion electric propulsion system; when the xenon gas cylinder pressure information does not meet the preset pressure information, according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the asynchronous control mode, adjust the gas supply situation of the gas supply control of the ion electric propulsion system.

[0073] The synchronous-asynchronous autonomous switching strategy of the embodiment of the present application is also called the automatic selection of synchronous-asynchronous control. The xenon bottle pressure information includes the xenon bottle pressure value, and the preset pressure information includes the preset pressure value; the xenon bottle pressure information satisfies the preset pressure information, which means that the xenon bottle pressure value is less than the preset pressure value; the xenon bottle pressure information does not satisfy the preset pressure information, which means that the xenon bottle pressure value is not less than the preset pressure value. The synchronous-asynchronous autonomous switching strategy of the pressure regulating module: the xenon bottle pressure of the ion electric propulsion is used as the front-stage pressure of the storage and supply subsystem. With the change of gas usage and ambient temperature, the front-stage pressure, i.e., the xenon bottle pressure, covers a range of 0.1Mpa~15Mpa. Therefore, when the xenon bottle pressure value is large, i.e., the xenon bottle pressure value is not less than the preset pressure value, the asynchronous control method is selected to mainly ensure the control accuracy; when the xenon bottle pressure value is small, i.e., the xenon bottle pressure value is less than the preset pressure value, the synchronous control method is selected to mainly ensure the control efficiency. The synchronous-asynchronous autonomous switching strategy minimizes the requirements for valve switch life; the synchronous-asynchronous autonomous switching strategy can achieve the optimal control goals of control accuracy, control efficiency and valve life when the xenon cylinder pressure changes over a large range. The above xenon cylinder pressure value is the following pressure reducing valve outlet pressure HP2 or HP3, the above preset pressure value is the following pressure reducing valve mode switching pressure MPH, the above synchronous control method is the following synchronous opening control strategy, and the above asynchronous control method is the following asynchronous opening control strategy.

[0074] like Figure 2 and 3 As shown, the pressure regulating module is divided into main and backup branches, each branch consists of a self-locking valve, a pressure reducing valve, a pressure sensor, and two solenoid valves with a Bang-bang structure. The pressure regulating module has a first-level pressure reducing function from the high pressure of the xenon cylinder to the low pressure of the buffer cylinder. It is necessary to determine the pressure control method of the buffer cylinder. Figure 3 In the process of adjusting the pressure value PT of the buffer gas cylinder, a series of valve actions are used to control the pressure value PT of the buffer gas cylinder within the range of [LPL, LPH], and judgment and control are implemented every 100ms. The buffer gas cylinder has 3 pressure sensors, which are used to monitor the pressure value of the buffer gas cylinder. The redundant design is adopted to ensure that the system function is not affected when one or two pressure sensors fail.

[0075] Before the Bang-bang valve pressure regulation control starts, a 100 ms timer is started, and the buffer gas cylinder pressure value PT is selected. Specifically, when all three pressure sensors are normal, or when one pressure sensor fails (the data transmitted back by the faulty sensor is the maximum value), the strategy of taking the middle value can be adopted: select the middle value of the three buffer gas cylinder pressure values LP1, LP2, and LP3 as the pressure control target PT; when two pressure sensors fail, only the specified value can be selected as the pressure control target PT, and the specified value can be the buffer gas cylinder pressure value PT of the specified non-faulty pressure sensor. This control strategy is the optimal control in terms of working condition adaptability. The pressure control target PT is the buffer gas cylinder pressure value PT.

[0076] When the buffer gas cylinder pressure value PT > the control target upper limit LPH, close the two solenoid valves on the selected measurement path, that is, close the main path solenoid valve SV1 and SV3 or the backup path solenoid valve SV2 and SV4, and then enter the next stage; when the control target lower limit LPL ≤ the buffer gas cylinder pressure value PT ≤ the control target upper limit LPH, the two solenoid valves on the selected measurement path remain unchanged and do not act, and then enter the next stage.

[0077] When the buffer gas cylinder pressure value PT < the control target lower limit LPL, the buffer gas cylinder needs to be refilled, and the refilling process is divided into two branches. According to the different main and backup path selections, when the pressure HP3 or HP2 at the outlet of the pressure reducing valve is less than the pressure reducing valve mode switching pressure MPH, the synchronous opening control strategy of the two solenoid valves on the selected measurement path is adopted: adopt the synchronous refilling control strategy, and simultaneously open the main path solenoid valve SV1, SV3 or the backup path solenoid valve SV2, SV4, and then enter the next stage. When the pressure HP3 or HP2 at the outlet of the pressure reducing valve is greater than or equal to the pressure reducing valve mode switching pressure MPH, the asynchronous opening control strategy of the two solenoid valves on the selected measurement path is adopted: adopt the asynchronous refilling control strategy, first open the upper valve solenoid valve SV1 or SV2 of the Bang-bang structure and keep it open for TM1 time and then close it, and then open the lower valve solenoid valve SV3 or SV4 of the Bang-bang structure. During this process, collect the opening duration Tsv of the solenoid valve SV3 or SV4, and keep it open for TM2 time and then close the solenoid valve SV3 or SV4. If the buffer gas cylinder pressure value PT reaches the control target upper limit LPH within TM2 time, the solenoid valve SV3 or SV4 is closed in advance, and then enter the next stage.

[0078] The above control process is controlled every 100 ms. If the above control process is less than 100 ms, it can wait for 100 ms and then enter the next stage. When receiving the instruction to close the pressure closed-loop control, set the Bang-bang valve pressure regulation control flag == on. In the state where the Bang-bang valve pressure regulation control flag == on, judge whether the 100 ms timing time is reached. If so, return to the step of starting the 100 ms timing and enter the next judgment process; in the state where the Bang-bang valve pressure regulation control flag != on, further set the prohibition flag, and judge whether the self-locking valves LV1 or LV2 close the prohibition flag. If not, it is necessary to close the self-locking valves LV1 or LV2 at the outlet valve of the xenon gas cylinder T1, and close the solenoid valves SV1, SV3 or solenoid valves SV2, SV4 of the Bang-bang structure; if so, the solenoid valves SV1, SV3 or solenoid valves SV2, SV4 of the Bang-bang structure can be directly closed. Thus, the pressure regulation control ends.

[0079] Among them, the control target upper limit LPH represents the upper limit of the buffer gas cylinder pressure control, taking 0.208 MPa; the control target lower limit LPL represents the lower limit of the buffer gas cylinder pressure control, taking 0.192 MPa; the outlet pressure HP2 or HP3 of the pressure reducing valve is the outlet pressure value of the pressure reducing gauge; the pressure reducing valve mode switching pressure MPH for synchronous and asynchronous switching pressure takes 1.5 MPa; TM1 is the opening time of the Bang-bang valve asynchronous upper valve, taking 1 s; TM2 is the opening time of the Bang-bang valve asynchronous lower valve, taking 2 s; Tsv is the single opening duration of the solenoid valves SV3 or SV4.

[0080] In the flow rate regulation module, when the neutralizer passage fails, the operation of adjusting the gas supply according to the pressure compensation control scheme and the xenon gas cylinder pressure information can be: the system specific impulse reduction ≤ 0.8%, which can be ignored, and the working performance meets the design requirements; when the main cathode passage fails, the operation of adjusting the gas supply according to the pressure compensation control scheme and the xenon gas cylinder pressure information can be: reducing the buffer gas cylinder pressure by 0.156 Mpa in orbit, closing all three-way thermal throttles for temperature control, and the system specific impulse is reduced by about 10%; when the anode passage fails, the operation of adjusting the gas supply according to the pressure compensation control scheme and the xenon gas cylinder pressure information can be: reducing the buffer gas cylinder pressure by 0.156 MPa in orbit, closing all three-way thermal throttles for temperature control, and the system specific impulse is reduced by about 10%; the treatment measures are the same as those for the failure of the main cathode passage.

[0081] In the embodiments of the present application, for the gas supply control method of the ion electric propulsion system, the failure conditions of the ion thruster passage and the xenon cylinder pressure information for the gas supply control of the ion electric propulsion system are acquired; according to the failure conditions of the ion thruster passage, a pressure compensation control scheme for the gas supply control of the ion electric propulsion system is formulated; according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy, the gas supply situation of the gas supply control of the ion electric propulsion system is adjusted. The synchronous / asynchronous autonomous switching strategy of the present application achieves the optimal control objectives of gas supply accuracy, gas supply efficiency, and valve life; the present application proposes a pressure compensation control scheme for the single-point failure of the heating wire of the thermal throttler, that is, the failure of the ion thruster passage, so that the electric propulsion system still has the necessary working ability under the worst conditions.

[0082] The following are the device embodiments of the present invention, which can be used to execute the method embodiments of the present invention. For the details not disclosed in the device embodiments of the present invention, please refer to the method embodiments of the present invention.

[0083] Please refer to Figure 7 , which shows a schematic structural diagram of a gas supply control device for an ion electric propulsion system provided by an exemplary embodiment of the present invention. The device includes: an acquisition module 10000, a scheme formulation module 20000, and an adjustment module 30000.

[0084] The acquisition module 10000 is configured to acquire the failure conditions of the ion thruster passage and the xenon cylinder pressure information for the gas supply control of the ion electric propulsion system;

[0085] The scheme formulation module 20000 is configured to formulate a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the failure conditions of the ion thruster passage;

[0086] The adjustment module 30000 is configured to adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy.

[0087] According to a preferred implementation manner, the acquisition module 10000 is specifically configured to:

[0088] Acquire the failure of the neutralizer passage, the failure of the main cathode passage, or the failure of the anode passage for the gas supply control of the ion electric propulsion system;

[0089] Take the failure of the neutralizer passage, the failure of the main cathode passage, or the failure of the anode passage as the failure conditions of the ion thruster passage for the gas supply control of the ion electric propulsion system.

[0090] According to a preferred embodiment, the cathode path and the anode path are controlled separately. The cathode path includes the neutralizer path corresponding to the failure of the neutralizer path and the main cathode path corresponding to the failure of the main cathode path; the anode path failure corresponds to the anode path.

[0091] According to a preferred embodiment, the scheme formulation module 20000 is specifically configured to:

[0092] When the neutralizer path fails, the formulated pressure compensation control scheme is not to take any treatment measures in orbit;

[0093] When the main cathode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the anode thermal throttle corresponding to the anode path;

[0094] When the anode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the main cathode thermal throttle corresponding to the main cathode path.

[0095] According to a preferred embodiment, the adjustment module 30000 is specifically configured to:

[0096] The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or the asynchronous control mode of the gas supply control of the ion electric propulsion system;

[0097] When the xenon gas cylinder pressure information meets the preset pressure information, the gas supply situation of the gas supply control of the ion electric propulsion system is adjusted according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous control mode;

[0098] When the xenon gas cylinder pressure information does not meet the preset pressure information, the gas supply situation of the gas supply control of the ion electric propulsion system is adjusted according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the asynchronous control mode.

[0099] It should be noted that when the ion electric propulsion system gas supply control device provided in the above embodiment executes the ion electric propulsion system gas supply control method, only the above-mentioned division of each functional module is used as an example for illustration. In practical applications, the above functions can be allocated to different functional modules according to needs, that is, the internal structure of the device is divided into different functional modules to complete all or part of the functions described above. In addition, the ion electric propulsion system gas supply control device provided in the above embodiment and the ion electric propulsion system gas supply control method embodiment belong to the same concept, and the implementation process is detailed in the method embodiment, which will not be repeated here.

[0100] In the embodiment of the present application, the gas supply control device of the ion electric propulsion system acquires the failure condition of the ion thruster path and the xenon cylinder pressure information for the gas supply control of the ion electric propulsion system; formulates a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the failure condition of the ion thruster path; and adjusts the gas supply condition of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy. The synchronous / asynchronous autonomous switching strategy of the present application achieves the optimal control objectives of gas supply accuracy, gas supply efficiency, and valve life; the present application proposes a pressure compensation control scheme for the single-point failure of the heating wire of the thermal throttle, that is, the failure condition of the ion thruster path, so that the electric propulsion system still has the necessary working ability under the worst conditions.

[0101] The present invention also provides a computer-readable medium, on which program instructions are stored, and when the program instructions are executed by a processor, the gas supply control method for the ion electric propulsion system provided by each of the above method embodiments is implemented.

[0102] The present invention also provides a computer program product containing instructions, which when running on a computer, causes the computer to execute the gas supply control method for the ion electric propulsion system provided by each of the above method embodiments.

[0103] Please refer to Figure 8 , which is a schematic structural diagram of a terminal provided by an embodiment of the present application. The terminal may include: at least one processor 1001, at least one network interface 1004, a user interface 1003, a memory 1005, and at least one communication bus 1002.

[0104] Among them, the communication bus 1002 is used to realize the connection and communication between these components.

[0105] Among them, the user interface 1003 may include a display screen (Display) and a camera (Camera). Optionally, the user interface 1003 may further include a standard wired interface and a wireless interface.

[0106] Among them, the network interface 1004 may optionally include a standard wired interface and a wireless interface (such as a WI-FI interface).

[0107] Among them, the processor 1001 may include one or more processing cores. The processor 1001 connects various parts within the entire terminal through various interfaces and lines, and executes various functions of the terminal and processes data by running or executing instructions, programs, code sets, or instruction sets stored in the memory 1005, and by calling the data stored in the memory 1005. Optionally, the processor 1001 may be implemented in at least one hardware form of digital signal processing (DSP), field-programmable gate array (FPGA), or programmable logic array (PLA). The processor 1001 may integrate one or a combination of several of a central processing unit (CPU), a graphics processing unit (GPU), and a modem, etc. Among them, the CPU mainly processes the operating system, user interface, application programs, etc.; the GPU is responsible for rendering and drawing the content to be displayed on the display screen; the modem is used to process wireless communications. It can be understood that the above-mentioned modem may not be integrated into the processor 1001 and may be implemented separately by a single chip.

[0108] Among them, the memory 1005 may include random access memory (RAM) and may also include read-only memory. Optionally, the memory 1005 includes a non-transitory computer-readable storage medium. The memory 1005 can be used to store instructions, programs, code, code sets, or instruction sets. The memory 1005 may include a program storage area and a data storage area. Among them, the program storage area may store instructions for implementing the operating system, instructions for at least one function (such as touch function, sound playback function, image playback function, etc.), instructions for implementing the above-mentioned various method embodiments, etc.; the data storage area may store the data involved in the above-mentioned various method embodiments. Optionally, the memory 1005 may also be at least one storage device located far from the aforementioned processor 1001. As Figure 8 shown, the memory 1005, as a computer storage medium, may include an operating system, a network communication module, a user interface module, and an ion electric propulsion system gas supply control application program.

[0109] In Figure 8In the terminal shown, the user interface 1003 is mainly used to provide an interface for the user to input and obtain the data input by the user; while the processor 1001 can be used to call the ion electric propulsion system gas supply control application program stored in the memory 1005 and specifically perform the following operations:

[0110] Obtain the ion thruster path failure situation and xenon gas cylinder pressure information of the ion electric propulsion system gas supply control;

[0111] According to the ion thruster path failure situation, formulate a pressure compensation control scheme for the ion electric propulsion system gas supply control;

[0112] According to the pressure compensation control scheme, the xenon gas cylinder pressure information and the synchronous asynchronous autonomous switching strategy, adjust the gas supply situation of the ion electric propulsion system gas supply control.

[0113] In one embodiment, when the processor 1001 executes the operation of obtaining the ion thruster path failure situation of the ion electric propulsion system gas supply control, it specifically performs the following operations:

[0114] Obtain the neutralizer path failure, main cathode path failure or anode path failure of the ion electric propulsion system gas supply control;

[0115] Take the neutralizer path failure, the main cathode path failure or the anode path failure as the ion thruster path failure situation of the ion electric propulsion system gas supply control;

[0116] Among them, the cathode path and the anode path are controlled separately. The cathode path includes the neutralizer path corresponding to the neutralizer path failure and the main cathode path corresponding to the main cathode path failure; the anode path failure corresponds to the anode path.

[0117] In one embodiment, when the processor 1001 executes the operation of formulating the pressure compensation control scheme for the ion electric propulsion system gas supply control according to the ion thruster path failure situation, it specifically performs the following operations:

[0118] When the neutralizer path fails, the formulated pressure compensation control scheme is not to take treatment measures in orbit;

[0119] When the main cathode path fails, the formulated pressure compensation control scheme is to reduce the buffer gas cylinder pressure and close the neutralizer thermal throttle temperature control corresponding to the neutralizer path and the anode thermal throttle temperature control corresponding to the anode path;

[0120] When the anode path fails, the formulated pressure compensation control scheme is to reduce the buffer gas cylinder pressure and close the neutralizer thermal throttle temperature control corresponding to the neutralizer path and the main cathode thermal throttle temperature control corresponding to the main cathode path.

[0121] In one embodiment, when the processor 1001 executes the adjustment of the gas supply condition of the ion electric propulsion system supply control according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy, the following operations are specifically performed:

[0122] The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or the asynchronous control mode of the ion electric propulsion system supply control;

[0123] When the xenon gas cylinder pressure information meets the preset pressure information, adjust the gas supply condition of the ion electric propulsion system supply control according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous control mode;

[0124] When the xenon gas cylinder pressure information does not meet the preset pressure information, adjust the gas supply condition of the ion electric propulsion system supply control according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the asynchronous control mode.

[0125] In the embodiment of the present application, the ion electric propulsion system supply control method and device obtain the ion thruster path failure condition and the xenon gas cylinder pressure information of the ion electric propulsion system supply control; formulate a pressure compensation control scheme for the ion electric propulsion system supply control according to the ion thruster path failure condition; and adjust the gas supply condition of the ion electric propulsion system supply control according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy. The synchronous / asynchronous autonomous switching strategy of the present application realizes the optimal control objectives of gas supply accuracy, gas supply efficiency, and valve life; the present application proposes a pressure compensation control scheme for the single-point failure of the thermal throttler heating wire, that is, the ion thruster path failure condition, so that the electric propulsion system in the worst case still has the necessary working ability.

[0126] Those of ordinary skill in the art can understand that all or part of the processes of implementing the methods in the above embodiments can be completed by instructing relevant hardware through a computer program. The program can be stored in a computer-readable storage medium. When the program is executed, it can include the processes of the embodiments of the above methods. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only memory, or a random access memory, etc.

[0127] The above-disclosed are only the preferred embodiments of the present application. Of course, the scope of the rights of the present application cannot be limited by this. Therefore, equivalent changes made according to the claims of the present application still fall within the scope covered by the present application.

Claims

1. A gas supply control method for an ion electric propulsion system, characterized in that, It includes the following steps: Obtain the ion thruster path failure situation and xenon cylinder pressure information for the gas supply control of the ion electric propulsion system; Formulate a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the ion thruster path failure situation; Adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy; Among them, obtaining the ion thruster path failure situation of the gas supply control of the ion electric propulsion system includes: Obtain the neutralizer path failure, main cathode path failure, or anode path failure of the gas supply control of the ion electric propulsion system; Take the neutralizer path failure, the main cathode path failure, or the anode path failure as the ion thruster path failure situation of the gas supply control of the ion electric propulsion system; The cathode path and the anode path are controlled separately. The cathode path includes the neutralizer path corresponding to the neutralizer path failure and the main cathode path corresponding to the main cathode path failure; the anode path failure corresponds to the anode path; The formulating the pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the ion thruster path failure situation includes: When the neutralizer path fails, the formulated pressure compensation control scheme is not to take treatment measures in orbit; When the main cathode path fails, the formulated pressure compensation control scheme is to reduce the buffer gas cylinder pressure and close the neutralizer thermal throttle temperature control corresponding to the neutralizer path and the anode thermal throttle temperature control corresponding to the anode path; When the anode path fails, the formulated pressure compensation control scheme is to reduce the buffer gas cylinder pressure and close the neutralizer thermal throttle temperature control corresponding to the neutralizer path and the main cathode thermal throttle temperature control corresponding to the main cathode path; The adjusting the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy includes: The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or asynchronous control mode of the gas supply control of the ion electric propulsion system; the synchronous control mode includes: simultaneously opening the main path solenoid valve SV1 and the main path solenoid valve SV3 of the storage and supply subsystem, or simultaneously opening the backup path solenoid valve SV2 and the backup path solenoid valve SV4 of the storage and supply subsystem; the asynchronous control mode includes: first opening the solenoid valve SV1 or SV2 and closing it after a continuous time of TM1, and then opening the solenoid valve SV3 or SV4; When the xenon cylinder pressure information meets the preset pressure information, adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the synchronous control mode; When the xenon cylinder pressure information does not meet the preset pressure information, adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon cylinder pressure information, and the asynchronous control mode.

2. An air supply control device for an ion electric propulsion system, characterized in that, It includes: An acquisition module, configured to acquire the ion thruster path failure situation and the xenon gas cylinder pressure information of the gas supply control of the ion electric propulsion system; A scheme formulation module, configured to formulate a pressure compensation control scheme for the gas supply control of the ion electric propulsion system according to the ion thruster path failure situation; An adjustment module, configured to adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous / asynchronous autonomous switching strategy; Wherein, the acquisition module is specifically configured to: Acquire the neutralizer path failure, the main cathode path failure, or the anode path failure of the gas supply control of the ion electric propulsion system; Use the neutralizer path failure, the main cathode path failure, or the anode path failure as the ion thruster path failure situation of the gas supply control of the ion electric propulsion system; The cathode path and the anode path are controlled separately. The cathode path includes the neutralizer path corresponding to the neutralizer path failure and the main cathode path corresponding to the main cathode path failure; the anode path failure corresponds to the anode path; The scheme formulation module is specifically configured to: When the neutralizer path fails, the formulated pressure compensation control scheme is not to take any treatment measures in orbit; When the main cathode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the anode thermal throttle corresponding to the anode path; When the anode path fails, the formulated pressure compensation control scheme is to reduce the pressure of the buffer gas cylinder and close the temperature control of the neutralizer thermal throttle corresponding to the neutralizer path and the temperature control of the main cathode thermal throttle corresponding to the main cathode path; The adjustment module is specifically configured to: The synchronous / asynchronous autonomous switching strategy switches the synchronous control mode or the asynchronous control mode of the gas supply control of the ion electric propulsion system; The synchronous control mode includes: simultaneously opening the main path solenoid valve SV1 and the main path solenoid valve SV3 of the storage and supply subsystem, or simultaneously opening the backup path solenoid valve SV2 and the backup path solenoid valve SV4 of the storage and supply subsystem; The asynchronous control mode includes: first opening the solenoid valve SV1 or SV2, closing it after a continuous time TM1, and then opening the solenoid valve SV3 or SV4; When the xenon gas cylinder pressure information meets the preset pressure information, adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the synchronous control mode; When the xenon gas cylinder pressure information does not meet the preset pressure information, adjust the gas supply situation of the gas supply control of the ion electric propulsion system according to the pressure compensation control scheme, the xenon gas cylinder pressure information, and the asynchronous control mode.

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