High-precision thrust control method and system for electric propulsion system, medium and equipment

Abstract

The invention provides a high-precision thrust control method, system, medium and equipment for an electric propulsion system. The high-precision thrust control system comprises a valve, a buffer gas cylinder, a pressure sensor, a controller and the like. Through time sequence design, automatic gas supplementing operation is carried out before pressure closed-loop control is carried out in the ignition preparation stage, so that the pressure value of a buffer gas tank at the initial ignition stage is kept consistent; in the ignition process, a bang valve pressure closed-loop control program is automatically switched, the upper limit and the lower limit of the pressure of the buffer gas tank are adjusted in real time according to a thrust value fed back by whole satellite attitude and orbit control, and therefore high-precision thrust control over the Hall thruster is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of space electric propulsion, and specifically, to a high-precision thrust control method, system, medium and device for an electric propulsion system. Background Art

[0002] Generally, a space electric propulsion system stores a propulsion working medium in a high-pressure gas cylinder, and uses a self-locking valve to isolate the propulsion working medium from the system. After the self-locking valve is opened, the propulsion working medium is subjected to primary pressure reduction by a pressure reducing valve. The pressure of a downstream buffer gas tank is controlled by a pressure closed-loop control device. When the pressure of the buffer gas tank is lower than the lower limit value, the BANGBANG valve starts to supply gas. When the pressure of the buffer gas tank is higher than the upper limit value, the BANGBANG valve stops working, so as to realize the pressure regulation and control of the buffer gas tank.

[0003] The pressure closed-loop control method in the prior art has defects, that is, the initial pressure of the buffer gas tank is different before each ignition, which causes deviation in the output thrust of the electric thruster, and the upper and lower limits of the buffer gas tank pressure cannot be adjusted in real time according to the external feedback thrust value during the ignition process. Therefore, a high-precision thrust control technology for an electric propulsion system is needed.

[0004] Patent application document CN113738606A discloses a continuous variable thrust optimal control system and method for an ion electric propulsion system. This method can achieve the optimal working efficiency while completing the thrust demand value, and realize the optimal control of the ion electric propulsion system. During specific operation, the controller receives the thrust demand value issued by the upper computer in each control cycle, and receives the current thrust value returned by the thrust detection unit in each adjustment cycle. Only based on the thrust demand value and the current thrust value, through open-loop control of the anode flow rate and closed-loop control of the anode current and excitation current, the real-time optimal thrust control of the thruster is realized. However, this patent cannot completely solve the existing technical problems and cannot meet the requirements of the present invention. Summary of the Invention

[0005] Aiming at the defects in the prior art, the purpose of the present invention is to provide a high-precision thrust control method, system, medium and device for an electric propulsion system.

[0006] The high-precision thrust control method for an electric propulsion system provided by the present invention includes: Step 1: When the electric propulsion system starts to work, set the upper limit LPH of the buffer gas tank pressure and the lower limit LPL of the buffer gas tank pressure; Step 2: Judge the pressure LP collected by the pressure sensor. If LP < LPH, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Step 3: Perform closed-loop control on the pressure based on the lower pressure limit LPL and the upper pressure limit LPH of the buffer gas tank. If LP < LPL, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve. Step 4: Based on the thrust value real-time feedback from the overall satellite attitude and orbit control, obtain the adjusted upper pressure limit LPH1 and the adjusted lower pressure limit LPL1 of the buffer gas tank according to the fitting formula obtained from ground tests. Step 5: Replace LPH and LPL with LPH1 and LPL1, return to Step 3 to continue execution, and end the program when the orbit control countdown ends. Among them, the first solenoid valve and the second solenoid valve are connected in series. The downstream of the first solenoid valve and the second solenoid valve is connected to the buffer gas tank, and the downstream of the buffer gas tank is connected to the pressure sensor; the pressure sensor is installed on the buffer gas tank and is electrically connected to the controller for transmitting the collected pressure signal to the controller; the controller is electrically connected to the first solenoid valve and the second solenoid valve for controlling the opening and closing of the first solenoid valve and the second solenoid valve.

[0007] Preferably, Step 2 is an autonomous air replenishment operation performed during the ignition preparation stage. By opening and closing the first solenoid valve and the second solenoid valve, the pressure of the buffer gas tank is made to reach LPH.

[0008] Preferably, after Step 2, autonomously switch to the pressure closed-loop control program in Step 3 to perform closed-loop control on the pressure.

[0009] Preferably, the return to Step 3 and continue execution in Step 5 includes loop-executing the pressure closed-loop control and the adjustment of the upper and lower pressure limits until the orbit control countdown ends.

[0010] According to the high-precision thrust control system for an electric propulsion system provided by the present invention, it includes: Module M1: When the electric propulsion system starts to work, set the upper pressure limit LPH and the lower pressure limit LPL of the buffer gas tank. Module M2: Judge the pressure LP collected by the pressure sensor. If LP < LPH, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve. Module M3: Perform closed-loop control on the pressure based on the lower pressure limit LPL and the upper pressure limit LPH of the buffer gas tank. If LP < LPL, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve. Module M4: Based on the thrust value real-time feedback from the overall satellite attitude and orbit control, obtain the adjusted upper pressure limit LPH1 and the adjusted lower pressure limit LPL1 of the buffer gas tank according to the fitting formula obtained from ground tests. Module M5: Replace LPH and LPL with LPH1 and LPL1, trigger module M3, and end the program when the track control countdown ends; The first solenoid valve and the second solenoid valve are connected in series. A buffer gas tank is connected downstream of the first solenoid valve and the second solenoid valve. A pressure sensor is connected downstream of the buffer gas tank. The pressure sensor is installed on the buffer gas tank and electrically connected to the controller to transmit the collected pressure signal to the controller. The controller is electrically connected to the first solenoid valve and the second solenoid valve to control the opening and closing of the first solenoid valve and the second solenoid valve.

[0011] Preferably, module M2 is performed during the ignition preparation phase, by opening and closing the first solenoid valve and the second solenoid valve to bring the pressure of the buffer gas tank to LPH.

[0012] Preferably, the pressure closed-loop control program is automatically invoked from module M2 to module M3 to perform closed-loop control of the pressure.

[0013] Preferably, the trigger module M3 in module M5 includes cyclically executing closed-loop pressure control and adjusting the upper and lower pressure limits until the track control countdown ends.

[0014] According to the present invention, a computer-readable storage medium storing a computer program is provided, wherein when the computer program is executed by a processor, the steps of the high-precision thrust control method for the electric propulsion system are implemented.

[0015] The electronic device provided by the present invention includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the computer program is executed by the processor, it implements the steps of the high-precision thrust control method for the electric propulsion system.

[0016] Compared with the prior art, the present invention has the following beneficial effects: This invention achieves high-precision thrust control by using timing design to ensure a constant initial pressure value in the buffer gas tank before ignition. It can also autonomously switch modes, automatically switching to a bangbang valve pressure closed-loop control program after setting the initial pressure value in the buffer gas tank before ignition. During ignition, the upper and lower limits of the buffer gas tank pressure are adjusted in real time based on the thrust value fed back from the entire satellite attitude and orbit control system. Attached Figure Description

[0017] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a flowchart of the high-precision thrust control method for the electric propulsion system of the present invention; Figure 2Structural diagram of the pressure closed-loop control device for the electric propulsion system of the present invention; As shown in the figure: solenoid valve 1, solenoid valve 2, buffer gas tank 3, pressure sensor 4. Specific implementation mode

[0018] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can be made. These all belong to the protection scope of the present invention.

[0019] Embodiment 1 As Figure 1 shown, the present invention provides a high-precision thrust control method for an electric propulsion system, which is realized by a pressure closed-loop control device. The pressure closed-loop control device includes: solenoid valve 1, solenoid valve 2, buffer gas tank 3 and pressure sensor 4. The pressure of the buffer gas tank 3 is regulated through the closed-loop control of the pressure sensor 4.

[0020] Define the pressure collected by the pressure sensor 4 as LP.

[0021] The connection relationship between "solenoid valve 1, solenoid valve 2, buffer gas tank 3 and pressure sensor 4": As Figure 2 shown, solenoid valve 1 and solenoid valve 2 are connected in series, and the downstream is connected to the buffer gas tank 3. The downstream of the buffer gas tank 3 is connected to the pressure sensor 4. When the pressure sensor 4 monitors that the pressure of the buffer gas tank 3 is lower than LPL, solenoid valve 1 and solenoid valve 2 are opened; when the pressure sensor 4 monitors that the pressure of the buffer gas tank 3 is higher than LPH, solenoid valve 1 and solenoid valve 2 are closed; The control method includes the following steps: Step S1, when the electric propulsion system starts to work, set the upper limit of the pressure of the buffer gas tank 3 as LPH, and the lower limit of the pressure of the buffer gas tank 3 as LPL; Step S2, judge the pressure LP collected by the pressure sensor 4. If LP < LPH, open solenoid valve 1 and solenoid valve 2; if LP ≥ LPH, close solenoid valve 1 and solenoid valve 2; Step S3, enter the bangbang valve pressure closed-loop control program, and perform closed-loop control on the pressure according to the upper and lower limits of the pressure of the buffer gas tank 3. If LP < LPL, open solenoid valve 1 and solenoid valve 2; if LP ≥ LPH, close solenoid valve 1 and solenoid valve 2, and enter step S5; Step S4, according to the real-time feedback thrust value of the whole satellite attitude and orbit control, obtain the adjusted upper limit LPH1 and lower limit LPL1 of the pressure of the buffer gas tank 3 according to the fitting formula obtained from the ground test, and enter step S3; Step S5, wait for the end of the orbit control countdown, and the program ends.

[0022] Through the timing design, the initial pressure value of the buffer gas tank 3 before ignition is made constant in the present invention, so as to achieve high-precision thrust control. Among them, step S2 can achieve that before entering the bangbang valve pressure closed-loop control program, ignition will be carried out after the closed-loop control program, so the pressure value of the buffer gas tank 3 before ignition is constant at LPH.

[0023] The present invention can autonomously achieve mode switching. After setting the initial pressure value of the buffer gas tank 3 before ignition, it autonomously switches to the bangbang valve pressure closed-loop control program. During the ignition process, the upper and lower limits of the pressure of the buffer gas tank 3 are adjusted in real time according to the thrust value feedback by the whole satellite attitude and orbit control, so as to achieve high-precision thrust control.

[0024] Embodiment 2 The present invention also provides a high-precision thrust control system for an electric propulsion system, including: Module M1: When the electric propulsion system starts to work, set the upper limit LPH of the buffer gas tank pressure and the lower limit LPL of the buffer gas tank pressure; Module M2: Judge the pressure LP collected by the pressure sensor. If LP < LPH, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Module M3: Perform closed-loop control on the pressure according to the lower limit LPL of the buffer gas tank pressure and the upper limit LPH of the buffer gas tank pressure. If LP < LPL, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Module M4: Based on the thrust value feedback by the whole satellite attitude and orbit control in real time, obtain the adjusted upper limit LPH1 of the buffer gas tank pressure and the adjusted lower limit LPL1 of the buffer gas tank pressure according to the fitting formula obtained from the ground test; Module M5: Replace LPH and LPL with LPH1 and LPL1, trigger Module M3, and end the program when the orbit control countdown ends; Among them, the first solenoid valve and the second solenoid valve are connected in series. The downstream of the first solenoid valve and the second solenoid valve is connected to the buffer gas tank, and the downstream of the buffer gas tank is connected to the pressure sensor; the pressure sensor is installed on the buffer gas tank and is electrically connected to the controller for transmitting the collected pressure signal to the controller; the controller is electrically connected to the first solenoid valve and the second solenoid valve for controlling the opening and closing of the first solenoid valve and the second solenoid valve.

[0025] Module M2 is carried out in the ignition preparation stage. By opening and closing the first solenoid valve and the second solenoid valve, the pressure of the buffer gas tank reaches LPH. After Module M2, the pressure closed-loop control program of Module M3 is autonomously called to perform closed-loop control on the pressure. The trigger Module M3 in Module M5 includes repeatedly executing the pressure closed-loop control and the adjustment of the pressure upper and lower limits until the orbit control countdown ends.

[0026] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0027] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A high-precision thrust control method for an electric propulsion system, characterized in that, including: Step 1: When the electric propulsion system starts to work, set the upper limit LPH and the lower limit LPL of the buffer gas tank pressure; Step 2: Judge the pressure LP collected by the pressure sensor. If LP < LPH, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Step 3: Perform closed-loop control on the pressure according to the lower limit LPL and the upper limit LPH of the buffer gas tank pressure. If LP < LPL, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Step 4: According to the thrust value real-time feedback of the whole satellite attitude and orbit control, obtain the adjusted upper limit LPH1 and the adjusted lower limit LPL1 of the buffer gas tank pressure based on the fitting formula obtained from the ground test; Step 5: Replace LPH and LPL with LPH1 and LPL1, return to Step 3 to continue execution, and end the program when the orbit control countdown ends; Wherein, the first solenoid valve and the second solenoid valve are connected in series. The downstream of the first solenoid valve and the second solenoid valve is connected to the buffer gas tank, and the downstream of the buffer gas tank is connected to the pressure sensor; the pressure sensor is installed on the buffer gas tank and is electrically connected to the controller for transmitting the collected pressure signal to the controller; the controller is electrically connected to the first solenoid valve and the second solenoid valve for controlling the opening and closing of the first solenoid valve and the second solenoid valve.

2. The high-precision thrust control method for an electric propulsion system according to claim 1, characterized in that, Step 2 is an autonomous gas replenishment operation during the ignition preparation stage. By opening and closing the first solenoid valve and the second solenoid valve, the pressure of the buffer gas tank reaches LPH.

3. The high-precision thrust control method for an electric propulsion system according to claim 1, characterized in that, Autonomously switch to the pressure closed-loop control program of Step 3 after Step 2, so as to perform closed-loop control on the pressure.

4. The high-precision thrust control method for an electric propulsion system according to claim 1, characterized in that, The return to Step 3 and continue execution in Step 5 includes loop-executing the pressure closed-loop control and the pressure upper and lower limit adjustment until the orbit control countdown ends.

5. A high-precision thrust control system for an electric propulsion system, characterized in that, including: Module M1: When the electric propulsion system starts to work, set the upper limit LPH and the lower limit LPL of the buffer gas tank pressure; Module M2: Judge the pressure LP collected by the pressure sensor. If LP < LPH, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Module M3: Perform closed-loop control on the pressure according to the lower limit LPL and the upper limit LPH of the buffer gas tank pressure. If LP < LPL, open the first solenoid valve and the second solenoid valve; if LP ≥ LPH, close the first solenoid valve and the second solenoid valve; Module M4: According to the thrust value real-time feedback of the whole satellite attitude and orbit control, obtain the adjusted upper limit LPH1 and the adjusted lower limit LPL1 of the buffer gas tank pressure based on the fitting formula obtained from the ground test; Module M5: Replace LPH and LPL with LPH1 and LPL1, trigger Module M3, and end the program when the orbit control countdown ends; The first solenoid valve and the second solenoid valve are connected in series. A buffer gas tank is connected downstream of the first solenoid valve and the second solenoid valve. A pressure sensor is connected downstream of the buffer gas tank. The pressure sensor is installed on the buffer gas tank and electrically connected to the controller to transmit the collected pressure signal to the controller. The controller is electrically connected to the first solenoid valve and the second solenoid valve to control the opening and closing of the first solenoid valve and the second solenoid valve.

6. The high-precision thrust control system for an electric propulsion system according to claim 5, characterized in that, Module M2 is performed during the ignition preparation phase, by opening and closing the first and second solenoid valves to bring the pressure in the buffer tank to LPH.

7. The high-precision thrust control system for an electric propulsion system according to claim 5, characterized in that, The pressure closed-loop control program of module M3 is automatically called after module M2 to perform closed-loop control of the pressure.

8. The high-precision thrust control system for an electric propulsion system according to claim 5, characterized in that, The trigger module M3 in module M5 includes cyclic execution of pressure closed-loop control and pressure upper and lower limit adjustment until the track control countdown ends.

9. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the steps of the high-precision thrust control method for an electric propulsion system as described in any one of claims 1 to 4.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the computer program is executed by the processor, it implements the steps of the high-precision thrust control method for an electric propulsion system as described in any one of claims 1 to 4.

Images