Micro-propulsion system for ground air floating satellite simulator and forming method of micro-propulsion system

Abstract

The invention provides a micro-propulsion system for a ground air floating satellite simulator and a forming method of the micro-propulsion system, and relates to the technical field of spacecraft ground tests. In the present application, the micro-propulsion system comprises: a gas nozzle; a solenoid valve; the output end of the micro-propulsion control assembly is connected with the electromagnetic valve, and the micro-propulsion control assembly is used for controlling whether the electromagnetic valve is opened or not; the communication transceiving module is used for communicating with a satellite service computer of a simulation satellite so as to receive a thrust value calculated by the satellite service computer, and sending the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines corresponding nozzle switching time based on the thrust value; therefore, the gas nozzle is controlled by the electromagnetic valve to output gas flow within the nozzle switching time, so that thrust corresponding to the thrust value is provided for the ground air floating satellite simulator. Based on the content, the problem that in the prior art, the cost of a micro-propulsion system is high can be solved.

Description

Technical Field

[0001] The present application relates to the technical field of spacecraft ground testing, and in particular to a micro-propulsion system for a ground-based air-floating satellite simulator and a method for forming the same. Background Art

[0002] With the rapid development of space technology, the application areas of satellites are also expanding. The movement of ground-based air-bearing satellite simulators requires the use of an air-bearing platform. This platform simulates the satellite's operating environment in space on the ground, providing important support for satellite design and testing. The design of a micro-propulsion system for ground-based air-bearing satellite simulators is a key technology, providing tiny but precise thrust to adjust the simulated satellite's attitude and orbit. Therefore, it is essential to design a micro-propulsion system for the air-bearing satellite simulator to achieve its movement on the marble platform.

[0003] Among them, in the micro-propulsion system of the ground-based air-floating satellite simulator, multiple factors need to be considered. First, it is necessary to determine the appropriate propulsion system type to meet the needs of the ground-based air-floating satellite simulator. Second, it is necessary to design a reasonable propulsion system structure, including thrusters, propellant storage and supply systems, etc. Currently, micro-propulsion systems have been widely used in the field of satellite engineering. Traditional micro-propulsion systems mainly rely on chemical propellants to generate thrust, but this propulsion system has some shortcomings, such as the difficulty of propellant storage and supply, the inability to replenish propellant after depletion, and its relatively complex structure and high cost, that is, it has a high cost problem. Summary of the Invention

[0004] In view of this, the purpose of the present application is to provide a micro-propulsion system for a ground-based air-floating satellite simulator and a method for forming the same, so as to improve the problem of high cost of micro-propulsion systems in the prior art.

[0005] To achieve the above objectives, this application adopts the following technical solutions: A micro-propulsion system for a ground-based air-floating satellite simulator, comprising: A gas nozzle, wherein the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle is used to output airflow to propel the ground-based air-floating satellite simulator to move; A solenoid valve, wherein the solenoid valve is provided in conjunction with the gas nozzle, and the solenoid valve is used to control whether the gas nozzle outputs airflow to drive the ground-based air-floating satellite simulator to move; a micro-propulsion control component, wherein an output end of the micro-propulsion control component is connected to the solenoid valve, and the micro-propulsion control component is used to control whether the solenoid valve is opened, so as to control whether the gas nozzle outputs airflow; A communication transceiver module, wherein the output end of the communication transceiver module is connected to the input end of the micro-propulsion control component, and the communication transceiver module is used to communicate with the satellite service computer of the simulated satellite to receive the thrust value calculated by the satellite service, and send the thrust value to the micro-propulsion control component, so that the micro-propulsion control component determines the corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output airflow within the nozzle switching time through the solenoid valve, so as to provide the ground air-floating satellite simulator with thrust corresponding to the thrust value.

[0006] In a preferred embodiment of the present application, in the micro-propulsion system for the ground-based air-floating satellite simulator, the micro-propulsion control component includes: a microcontroller, wherein an input end of the microcontroller is connected to the communication transceiver module, configured to receive the thrust value calculated by the satellite service through the communication transceiver module, determine a corresponding nozzle switching time based on the thrust value, and output a corresponding control signal based on the nozzle switching time; An optocoupler relay, wherein an input end of the optocoupler relay is connected to the microcontroller, the optocoupler relay is used to receive a control signal from the microcontroller, and when the control signal is high, the optocoupler relay outputs a high level; MOS tube, wherein the gate of the MOS tube is connected to the output end of the optocoupler relay, and when the optocoupler relay outputs a high level, the source and drain of the MOS tube are connected to control the solenoid valve to open.

[0007] In a preferred embodiment of the present application, in the micro-propulsion system for the ground-based air-floating satellite simulator, the micro-propulsion control component further comprises a diode and an output resistor forming an output circuit with the source and drain of the MOS tube; Wherein, when the source and drain of the MOS tube are not conducting, the voltage across the output resistor is equal to the cut-off voltage of the diode, so that the solenoid valve does not open; When the source and drain of the MOS transistor are turned on, a voltage drop of a high-level target voltage is formed across the output resistor, causing the solenoid valve to open.

[0008] In a preferred embodiment of the present application, the micro-propulsion system for the ground-based air-floating satellite simulator further comprises: High-pressure gas tank, wherein the high-pressure gas tank is used to store high-pressure gas; A pressure reducing valve, wherein the pressure reducing valve is connected to the high-pressure gas tank and the gas nozzle respectively, and the pressure reducing valve is used to reduce the pressure of the airflow output from the high-pressure gas tank and then output it to the gas nozzle.

[0009] On the basis of the above, the present application further provides a method for forming a micro-propulsion system, which is used to form the above-mentioned micro-propulsion system for a ground-based air-floating satellite simulator, wherein the method for forming the micro-propulsion system comprises: Determining a gas nozzle, wherein the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle is used to output airflow to propel the ground-based air-floating satellite simulator to move; Determine a solenoid valve and set the solenoid valve in conjunction with the gas nozzle, wherein the solenoid valve is used to control whether the gas nozzle outputs airflow to propel the ground-based air-floating satellite simulator to move; Determining a micro-propulsion control component and connecting an output end of the micro-propulsion control component to the solenoid valve, wherein the micro-propulsion control component is used to control whether the solenoid valve is open to control whether the gas nozzle outputs airflow; A communication transceiver module is determined, and an output end of the communication transceiver module is connected to an input end of the micro-propulsion control assembly, wherein the communication transceiver module is used to communicate with a satellite service computer of the simulated satellite to receive a thrust value calculated by the satellite service computer, and send the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines a corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output an airflow within the nozzle switching time through the solenoid valve, thereby providing a thrust corresponding to the thrust value to the ground air-bearing satellite simulator.

[0010] In a preferred embodiment of the present application, in the method for forming the micro-propulsion system, the step of determining the gas nozzle includes: In response to a target operation, determining an inlet pressure, a convergence angle, and a divergence angle of the gas nozzle, wherein the target operation includes a pressure configuration operation performed by a target user; determining a throat area of ​​a gas nozzle based on the inlet pressure; Based on the throat area, the convergence angle and the divergence angle, a gas nozzle is determined, wherein the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle includes three parts: a convergence zone, a throat and a divergence zone. When the gas enters the convergence zone of the Laval nozzle, the area of ​​the nozzle cross section gradually decreases, and when it reaches the throat, the area of ​​the nozzle cross section reaches the minimum. During this process, the gas is continuously accelerated, and the flow rate reaches the maximum when it reaches the throat. After passing through the throat, the gas enters the divergence zone, the area of ​​the nozzle cross section gradually increases, and the flow rate gradually increases.

[0011] In a preferred embodiment of the present application, in the method for forming the micro-propulsion system, the step of determining the throat area of ​​the gas nozzle based on the inlet pressure includes: Determine the Mach number at the outlet of the gas nozzle based on the inlet pressure of the gas nozzle, the ambient pressure and the air heat ratio; determining an outlet cross-sectional temperature of the gas nozzle based on the inlet temperature of the gas nozzle, the air heat ratio, and the outlet Mach number; determining a sound velocity at an outlet section of a gas nozzle based on an air gas constant, the air heat ratio, and the outlet section temperature; determining an outlet gas velocity based on the outlet Mach number and the outlet cross-sectional sound velocity; determining a flow mass ratio based on a target thrust and an outlet gas velocity, wherein the target thrust is achieved in response to the target operation; determining an outlet area based on the flow mass ratio, the air gas constant, the outlet cross-sectional temperature, the outlet gas velocity, and the ambient pressure, wherein the outlet area has a positive correlation with the flow mass ratio, the air gas constant, and the outlet cross-sectional temperature, and has a negative correlation with the outlet area and the outlet gas velocity and the ambient pressure; A throat area is determined based on the outlet area, the outlet Mach number, and the air heat ratio.

[0012] In a preferred embodiment of the present application, in the method for forming the micro-propulsion system, the step of determining the outlet Mach number of the gas nozzle based on the inlet pressure of the gas nozzle, the ambient pressure, and the air heat ratio includes: determining a ratio between an inlet pressure of a gas nozzle and an ambient pressure to obtain a first ratio, and determining a difference between the air heat ratio and a first parameter to obtain a first difference; determining a ratio between a second parameter and the first difference to obtain a second ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; determining a ratio between the first difference and the air heat ratio to obtain a third ratio, and performing a power operation on the first ratio based on the third ratio to obtain a first power operation result; determining a difference between the first power operation result and the first parameter to obtain a second difference; An outlet Mach number of the gas nozzle is determined based on the second ratio and the second difference, wherein the outlet Mach number has a positive correlation with both the second ratio and the second difference.

[0013] In a preferred embodiment of the present application, in the method for forming the micro-propulsion system, the step of determining the outlet cross-sectional temperature of the gas nozzle based on the inlet temperature of the gas nozzle, the air heat ratio, and the outlet Mach number includes: determining a difference between the air heat ratio and a first parameter to obtain a first difference; determining a ratio between the first difference and a second parameter to obtain a fourth ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; performing a power operation on the outlet Mach number based on the second parameter to obtain a second power operation result, and determining a product between the fourth ratio and the second power operation result, and determining a sum of the first parameter and the product; The ratio between the inlet temperature of the gas nozzle and the sum is determined to obtain the outlet cross-sectional temperature.

[0014] In a preferred embodiment of the present application, in the method for forming the micro-propulsion system, the step of determining the throat area based on the outlet area, the outlet Mach number, and the air heat ratio includes: Determining a difference between the air heat ratio and a first parameter to obtain a first difference, and determining a sum between the air heat ratio and the first parameter to obtain a first sum; determining a ratio between the first difference and the first sum to obtain a fifth ratio; determining a ratio between the first difference and a second parameter to obtain a sixth ratio, and determining a ratio between the first sum and the second parameter to obtain a seventh ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; performing a power operation on the outlet Mach number based on the second parameter to obtain a second power operation result, determining a product between the sixth ratio and the second power operation result, and determining a sum between the first parameter and the product to obtain a second sum; determining a ratio between the second sum and the seventh ratio to obtain an eighth ratio, and performing a power operation on the eighth ratio based on the fifth ratio to obtain a third power operation result; The throat area is determined based on the outlet area, the outlet Mach number, and the result of the third power operation, wherein the throat area has a positive correlation with the outlet area, the outlet Mach number, and the result of the third power operation.

[0015] In the micro-propulsion system for a ground-based air-floating satellite simulator and its formation method provided in the present application, the micro-propulsion system includes: a gas nozzle; a solenoid valve; a micro-propulsion control assembly, wherein the output end of the micro-propulsion control assembly is connected to the solenoid valve, and the micro-propulsion control assembly is used to control whether the solenoid valve is open; and a communication transceiver module, wherein the communication transceiver module is used to communicate with the satellite computer of the simulated satellite to receive the thrust value calculated by the satellite computer and send the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines the corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output airflow within the nozzle switching time through the solenoid valve to provide the ground-based air-floating satellite simulator with thrust corresponding to the thrust value. Based on the above content, a simplified configuration of the micro-propulsion system can be achieved, so that the structure of the micro-propulsion system can be simpler, thereby having a lower cost, thereby improving the problem of high cost of micro-propulsion systems in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings.

[0017] Figure 1 This is a schematic diagram of the application principle of the micro-propulsion system for a ground-based air-floating satellite simulator provided in an embodiment of the present application.

[0018] Figure 2 A block diagram of a micro-propulsion system for a ground-based air-floating satellite simulator provided in an embodiment of the present application.

[0019] Figure 3 A schematic flow chart of a method for forming a micro-propulsion system according to an embodiment of the present application. DETAILED DESCRIPTION

[0020] To make the objectives, technical solutions, and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Generally, the components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0021] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for protection, but merely represents selected embodiments of the present application. All other embodiments obtained by persons of ordinary skill in the art based on the embodiments in the present application without creative work are within the scope of protection of the present application.

[0022] An embodiment of the present application provides a micro-propulsion system for a ground-based air-floating satellite simulator, comprising a gas nozzle, a solenoid valve, a micro-propulsion control component, and a communication transceiver module.

[0023] In detail, the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle is used to output an airflow to propel the ground-based air-floating satellite simulator to move. The solenoid valve is arranged in conjunction with the gas nozzle, and the solenoid valve is used to control whether the gas nozzle outputs an airflow to propel the ground-based air-floating satellite simulator to move. The output end of the micro-propulsion control component is connected to the solenoid valve, and the micro-propulsion control component is used to control whether the solenoid valve is open to control whether the gas nozzle outputs an airflow. The output end of the communication transceiver module is connected to the input end of the micro-propulsion control component, and the communication transceiver module (which can be a transceiver chip, the model can be MAX3074E, such as Figure 1 As shown) is used to simulate the satellite's satellite computer (such as Figure 1 The micro-propulsion control assembly is configured to communicate with a satellite platform (as shown in the figure) to receive a thrust value calculated by a satellite service, and send the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines a corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output an airflow within the nozzle switching time through the solenoid valve, so as to provide the ground air-bearing satellite simulator with a thrust corresponding to the thrust value.

[0024] Based on the above content, a simplified configuration of the micro-propulsion system can be achieved, so that the structure of the micro-propulsion system can be simpler, thereby having a lower cost, thereby improving the high cost problem of the micro-propulsion system in the prior art.

[0025] It can be understood that, in an alternative embodiment, in order to make the control accuracy of the micro-propulsion control component higher and achieve high-precision control of the airflow output by the gas nozzle, the micro-propulsion control component may include a microcontroller, an optocoupler relay and a MOS tube.

[0026] Specifically, the input of the microcontroller is connected to the communication transceiver module, and is configured to receive the thrust value calculated by the satellite service through the communication transceiver module, determine the corresponding nozzle switching time based on the thrust value, and output a corresponding control signal based on the nozzle switching time. The input of the optocoupler relay is connected to the microcontroller, and the optocoupler relay is configured to receive the control signal from the microcontroller. When the control signal is at a high level, the optocoupler relay outputs a high level. The gate of the MOS transistor is connected to the output of the optocoupler relay. When the optocoupler relay outputs a high level, the source and drain of the MOS transistor are conductive, thereby controlling the opening of the solenoid valve.

[0027] It is understandable that, in an alternative embodiment, the micro-propulsion control component further includes a diode and an output resistor that form an output loop with the source and drain of the MOS transistor.

[0028] Specifically, when the source and drain of the MOS transistor are not conducting, the voltage across the output resistor is equal to the cutoff voltage of the diode, preventing the solenoid valve from opening. When the source and drain of the MOS transistor are conducting, a voltage drop of a high-level target voltage is formed across the output resistor, causing the solenoid valve to open.

[0029] It is understood that the specific connection method of the output resistor and the diode is not limited, as long as it meets the above requirements. For example, in an alternative embodiment, the drain of the MOS transistor can be connected to a power supply having the target voltage, the source of the MOS transistor can be connected to the first end of the output resistor, the second end of the output resistor can be connected to the anode of the diode, and the cathode of the diode can be grounded.

[0030] It is understandable that, in an alternative embodiment, the optocoupler relay, the MOS tube, the solenoid valve and the gas nozzle can be multiple groups. That is, each group includes one optocoupler relay, one MOS tube, one solenoid valve and one gas nozzle. In this way, each gas nozzle can be controlled separately to complete the corresponding thrust output. In other words, when a gas nozzle is required to provide thrust, that is, to control the corresponding solenoid valve to open, the corresponding port of the microcontroller outputs a high level, so that the optocoupler relay outputs a high level, driving the MOS tube to turn on. Among them, when the MOS tube is not turned on, the two ends of the output resistor only have the cut-off voltage of the diode, which is close to 0V. When the MOS tube is turned on, the two ends of the output resistor form a loop, and a 12V voltage drop is formed at both ends, which can drive the solenoid valve to open.

[0031] It is understandable that, in an alternative embodiment, the micro-propulsion system for the ground-based air-floating satellite simulator may further include a high-pressure gas tank and a pressure reducing valve.

[0032] Specifically, the high-pressure gas tank is used to store high-pressure gas. The pressure reducing valve is connected to the high-pressure gas tank and the gas nozzle, respectively, and is used to reduce the pressure of the gas flow output from the high-pressure gas tank before delivering it to the gas nozzle. For example, the high-pressure gas tank stores 15MPa of high-pressure gas, which is then reduced to approximately 0.4MPa by the pressure reducing valve and supplied to the gas nozzle.

[0033] It is understandable that, in an alternative embodiment, the high-pressure gas tank may also be connected to a charging valve, so that the gas in the high-pressure gas tank can be replenished through the charging valve.

[0034] Combine Figure 3 The present application also provides a method for forming a micro-propulsion system. The method can be used to form the micro-propulsion system for the ground-based air-floating satellite simulator. The steps of the method are as follows.

[0035] Step S110: determining the gas nozzle.

[0036] In the embodiments of the present application, a gas nozzle can be identified. The gas nozzle includes a structure similar to a Laval nozzle, which is used to output airflow to propel the ground-based air-floating satellite simulator. It should be noted that different Laval nozzles have different output properties, so the appropriate gas nozzle needs to be determined based on actual needs.

[0037] Step S120: Determine a solenoid valve and configure the solenoid valve in conjunction with the gas nozzle.

[0038] In the embodiment of the present application, a solenoid valve can be determined and configured in conjunction with the gas nozzle, wherein the solenoid valve is used to control whether the gas nozzle outputs airflow to propel the ground-based air-floating satellite simulator to move.

[0039] Step S130 , determining a micro-propulsion control component, and connecting an output end of the micro-propulsion control component to the solenoid valve.

[0040] In the embodiment of the present application, a micro-propulsion control component can be determined, and an output end of the micro-propulsion control component is connected to the solenoid valve, wherein the micro-propulsion control component is used to control whether the solenoid valve is open to control whether the gas nozzle outputs airflow.

[0041] Step S140: Determine a communication transceiver module, and connect the output end of the communication transceiver module to the input end of the micro-propulsion control component.

[0042] In an embodiment of the present application, a communication transceiver module can be determined, and the output of the communication transceiver module can be connected to the input of the micro-propulsion control assembly. The communication transceiver module is configured to communicate with the satellite control computer of the simulated satellite to receive a thrust value calculated by the computer, and to transmit the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines a corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output airflow within the nozzle switching time through the solenoid valve, thereby providing the ground-based air-bearing satellite simulator with thrust corresponding to the thrust value.

[0043] It can be understood that, in the above-mentioned step S110, the specific method of determining the gas nozzle is not limited and can be selected according to actual needs. For example, in an alternative embodiment, in order to improve the reliability of the determined gas nozzle so that the ground-based air-floating satellite simulator can be reliably pushed, the above-mentioned step S110 can further include step S111, step S112 and step S113, and the specific content of each step is described below.

[0044] Step S111 : determining the inlet pressure, convergence angle, and divergence angle of the gas nozzle in response to the target operation.

[0045] In an embodiment of the present application, the inlet pressure, convergence angle and divergence angle of the gas nozzle can be determined in response to a target operation. The target operation includes a pressure configuration operation performed by a target user. That is, the target user can configure the inlet pressure, convergence angle and divergence angle according to actual needs. For example, in a specific application example, the inlet pressure can be 0.4 MPa. In addition, since there is no boundary layer separation, the convergence angle is not of critical importance; on the contrary, in order to limit the performance loss caused by boundary layer separation, the divergence angle must be as small as possible. For example, the convergence angle can be 15° and the divergence angle can be 30°.

[0046] Step S112: determining the throat area of ​​the gas nozzle based on the inlet pressure.

[0047] In an embodiment of the present application, after the inlet pressure is determined, the throat area of ​​the gas nozzle is determined based on the inlet pressure.

[0048] Step S113: determining a gas nozzle based on the throat area, the convergence angle, and the divergence angle.

[0049] In an embodiment of the present application, after determining the throat area, the convergence angle, and the divergence angle, a gas nozzle can be determined based on the throat area, the convergence angle, and the divergence angle (for example, operations such as manufacturing or screening of gas nozzles can be performed according to the throat area, the convergence angle, and the divergence angle). The gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle includes three parts: a convergence region, a throat, and a divergence region. When the gas enters the convergence region of the Laval nozzle, the cross-sectional area of ​​the nozzle gradually decreases, and when it reaches the throat, the cross-sectional area of ​​the nozzle reaches its minimum. During this process, the gas is continuously accelerated, and the flow rate reaches its maximum when it reaches the throat. After passing through the throat, the gas enters the divergence region, and the cross-sectional area of ​​the nozzle gradually increases, and the flow rate gradually increases.

[0050] It can be understood that, in the above-mentioned step S112, the specific method of determining the throat area of ​​the gas nozzle based on the inlet pressure is not limited and can be selected according to actual needs. For example, in an alternative embodiment, in order to ensure that the reliability of the determined throat area of ​​the gas nozzle is relatively high, the above-mentioned step S112 can further include the following steps S112a, step S112b, step S112c, step S112d, step S112e, step S112f and step S112g, and the specific content of each step is described below.

[0051] Step S112a: determining the outlet Mach number of the gas nozzle based on the inlet pressure of the gas nozzle, the ambient pressure, and the air heat ratio.

[0052] In the embodiment of the present application, the outlet Mach number of the gas nozzle may be determined based on the inlet pressure of the gas nozzle, the ambient pressure, and the air heat ratio.

[0053] Step S112b: determining the outlet cross-sectional temperature of the gas nozzle based on the inlet temperature of the gas nozzle, the air heat ratio, and the outlet Mach number.

[0054] In the embodiment of the present application, after the outlet Mach number is obtained, the outlet cross-sectional temperature of the gas nozzle may be determined based on the inlet temperature of the gas nozzle, the air heat ratio, and the outlet Mach number.

[0055] Step S112c: determining the outlet cross-sectional sound velocity of the gas nozzle based on the air gas constant, the air heat ratio and the outlet cross-sectional temperature.

[0056] In the embodiment of the present application, after the outlet cross-sectional temperature is determined, the outlet cross-sectional sound velocity of the gas nozzle may be determined based on the air gas constant, the air heat ratio, and the outlet cross-sectional temperature.

[0057] Step S112d: determining the outlet gas velocity based on the outlet Mach number and the outlet cross-sectional sound velocity.

[0058] In the embodiment of the present application, after the outlet cross-sectional sound velocity is obtained, the outlet gas velocity can be determined based on the outlet Mach number and the outlet cross-sectional sound velocity.

[0059] Step S112e: determining the flow mass ratio based on the target thrust and the outlet gas velocity.

[0060] In an embodiment of the present application, after obtaining the flow-to-mass ratio, the flow-to-mass ratio can be determined based on the target thrust and the outlet gas velocity. The target thrust is obtained in response to the target operation. For example, in a specific application example, the target thrust can be 0.1N.

[0061] Step S112f, determining the outlet area based on the flow mass ratio, the air gas constant, the outlet cross-section temperature, the outlet gas velocity and the ambient pressure.

[0062] In the embodiment of the present application, after obtaining the flow rate mass ratio, the outlet area can be determined based on the flow rate mass ratio, the air gas constant, the outlet cross-sectional temperature, the outlet gas velocity, and the ambient pressure. The outlet area has a positive correlation with the flow rate mass ratio, the air gas constant, and the outlet cross-sectional temperature, and a negative correlation with the outlet gas velocity and the ambient pressure.

[0063] Step S112g: determining the throat area based on the outlet area, the outlet Mach number, and the air heat ratio.

[0064] In an embodiment of the present application, after the outlet area is obtained, the throat area may be determined based on the outlet area, the outlet Mach number, and the air heat ratio.

[0065] It is understood that, in the above-mentioned step S112a, the specific method of determining the outlet Mach number of the gas nozzle is not limited and can be selected according to actual needs. For example, in an alternative embodiment, in order to ensure the reliability of the determined outlet Mach number and the gas flow rate at the nozzle inlet can be approximately zero, the properties of the gas at the inlet are the properties of air at room temperature under a certain pressure. In this case, the above-mentioned step S112a can further include the following sub-steps: First, a ratio between an inlet pressure of a gas nozzle and an ambient pressure may be determined to obtain a first ratio, and a difference between the air heat ratio and a first parameter may be determined to obtain a first difference; Next, a ratio between a second parameter and the first difference may be determined to obtain a second ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; Then, a ratio between the first difference and the air heat ratio may be determined to obtain a third ratio, and a power operation may be performed on the first ratio based on the third ratio to obtain a first power operation result; Afterwards, a difference between the first power operation result and the first parameter may be determined to obtain a second difference; Finally, an outlet Mach number of the gas nozzle may be determined based on the second ratio and the second difference, wherein the outlet Mach number has a positive correlation with both the second ratio and the second difference.

[0066] For example, in a specific application scenario, the specific processing process of the above step S112a can refer to the following formula: ; in, is the inlet pressure, is the ambient pressure, is the exit Mach number, is the air heat ratio.

[0067] It is understood that, in the above step S112b, the specific method of determining the outlet cross-sectional temperature of the gas nozzle is not limited and can be selected according to actual needs. For example, in an alternative embodiment, in order to ensure the reliability of the determined outlet cross-sectional temperature, the above step S112a may further include the following sub-steps: First, a difference between the air heat ratio and a first parameter may be determined to obtain a first difference; Next, a ratio between the first difference and a second parameter may be determined to obtain a fourth ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; Then, based on the second parameter, the outlet Mach number may be subjected to a power operation to obtain a second power operation result, and a product between the fourth ratio and the second power operation result may be determined, and a sum of the first parameter and the product may be determined. Finally, the ratio between the inlet temperature of the gas nozzle and the sum is determined to obtain the outlet cross-sectional temperature.

[0068] For example, in a specific application scenario, the specific processing process of the above step S112b can refer to the following formula: ; in, is the inlet temperature, is the outlet section temperature.

[0069] For example, in a specific application scenario, the specific processing process of the above step S112c can refer to the following formula: ; in, is the sound velocity at the outlet section, is the gas constant of air.

[0070] For example, in a specific application scenario, the specific processing process of the above step S112d can refer to the following formula: ; in, is the outlet gas velocity.

[0071] For example, in a specific application scenario, the specific processing process of the above step S112e can refer to the following formula: ; in, is the flow-to-quality ratio, is the target thrust, such as 0.1N.

[0072] For example, in a specific application scenario, the specific processing process of the above step S112f can refer to the following formula: ; in, is the outlet area.

[0073] It is understood that in the above step S112g, the specific method of determining the throat area is not limited and can be selected according to actual needs. For example, in an alternative embodiment, in order to ensure the reliability of the determined throat area, the above step S112a can further include the following sub-steps: First, a difference between the air heat ratio and a first parameter may be determined to obtain a first difference, and a sum between the air heat ratio and the first parameter may be determined to obtain a first sum; Next, a ratio between the first difference and the first sum may be determined to obtain a fifth ratio; Then, a ratio between the first difference and the second parameter may be determined to obtain a sixth ratio, and a ratio between the first sum and the second parameter may be determined to obtain a seventh ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; Then, a power operation may be performed on the outlet Mach number based on the second parameter to obtain a second power operation result, a product between the sixth ratio and the second power operation result may be determined, and a sum value between the first parameter and the product may be determined to obtain a second sum value; Further, a ratio between the second sum and the seventh ratio may be determined to obtain an eighth ratio, and, based on the fifth ratio, the eighth ratio may be subjected to a power operation to obtain a third power operation result. Finally, the throat area can be determined based on the outlet area, the outlet Mach number and the third power operation result, wherein the throat area has a positive correlation with the outlet area, the outlet Mach number and the third power operation result.

[0074] For example, in a specific application scenario, the specific processing process of the above step S112g can refer to the following formula: ; in, is the throat area.

[0075] For the above-mentioned method of forming a micro-propulsion system, in a specific application scenario, the relevant parameters of the gas nozzle can be determined as shown in the following table (the throat diameter is determined based on the throat area):

[0076] In addition, the corresponding specific parameters can be determined according to the functional requirements and performance indicators of the micro-propulsion system, including board size, electrical interface, working voltage, etc. Among them, the external interface includes power interface, CAN communication interface, debugging interface, output interface, the working voltage of the microcontroller is selected from 5V and 3.3V, and the control voltage of the switching circuit is 12V. Moreover, according to the required voltage, such as the driving voltage of the solenoid valve, the reference voltage of the microcontroller, etc., a hierarchical voltage divider circuit can be designed as a power supply module to ensure that the system can maintain the power consumption requirements, and the AMS1117-3.3 model chip (DC / DC) is selected to convert 5V to 3.3V voltage. In addition, according to the voltage provided by the power supply module and the driving voltage requirement of the solenoid valve, the relay model can be selected as the optocoupler relay EL357N-G, which can eliminate the current jump of the traditional relay. The designed optocoupler relay-MOS tube control switch circuit (such as Figure 1In the solenoid valve driver module, when the microcontroller's GPIO output is high, the optocoupler relay outputs a high level, which is fed to the G terminal of the N-MOS transistor. This causes the voltage at the GS terminal to exceed 0, turning on the DS terminal. Simultaneously, a cutoff diode is added to the output resistor. When the DS terminal is not conducting, only the diode's cutoff voltage, close to 0V, appears across the output resistor. When the DS terminal is conducting, a loop is formed across the output resistor, resulting in a 12V voltage drop. This indicates that the thrust switch signal output by the microcontroller can drive the switching circuit, thereby controlling the on and off of the solenoid valve and, therefore, whether the gas nozzle outputs high-speed airflow. Furthermore, considering factors such as processing power, number of interfaces, and power consumption, the STM32F407 microcontroller was selected based on requirements. Based on the microcontroller's pin definition and peripheral circuit requirements, the peripheral circuits, including the power supply circuit, clock circuit, communication interface circuit, serial port download circuit, and switching circuit, were designed and connected to complete the schematic design. The schematic can then be converted into a PCB design. The dimensions of the micro-thrust control system's circuit board are planned based on the required structural dimensions. Layout design is performed according to layout rules, including placement of the microcontroller and other peripheral components. Considerations such as wiring, power distribution, and signal integrity are considered, ensuring that components within the same module are as centralized as possible. Signal routing is then performed according to the layout design, completing the micro-thrust control system's circuit board design. Copper fill is required to ensure current supply and ground shielding. The designed micro-thrust control system's circuit board dimensions can be 89 × 95 × 5.5 mm.

[0077] In summary, the micro-propulsion system for a ground-based air-floating satellite simulator and its formation method provided by the present application include: a gas nozzle; a solenoid valve; a micro-propulsion control assembly, wherein the output end of the micro-propulsion control assembly is connected to the solenoid valve, and the micro-propulsion control assembly is used to control whether the solenoid valve is open; and a communication transceiver module, wherein the communication transceiver module is used to communicate with the satellite computer of the simulated satellite to receive the thrust value calculated by the satellite computer and send the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines the corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output airflow within the nozzle switching time through the solenoid valve to provide the ground-based air-floating satellite simulator with thrust corresponding to the thrust value. Based on the above content, a simplified configuration of the micro-propulsion system can be achieved, so that the structure of the micro-propulsion system can be simpler, thereby having a lower cost, thereby improving the problem of high cost of micro-propulsion systems in the prior art.

[0078] The above description is merely a preferred embodiment of the present application and is not intended to limit the present application. Various modifications and variations are possible for those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present application shall be included within the scope of protection of the present application.

Claims

1. A micro-propulsion system for a ground-based air-floating satellite simulator, characterized in that: include: A gas nozzle, wherein the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle is used to output airflow to propel the ground-based air-floating satellite simulator to move; A solenoid valve, wherein the solenoid valve is provided in conjunction with the gas nozzle, and the solenoid valve is used to control whether the gas nozzle outputs airflow to drive the ground-based air-floating satellite simulator to move; a micro-propulsion control component, wherein an output end of the micro-propulsion control component is connected to the solenoid valve, and the micro-propulsion control component is used to control whether the solenoid valve is opened, so as to control whether the gas nozzle outputs airflow; A communication transceiver module, wherein the output end of the communication transceiver module is connected to the input end of the micro-propulsion control component, and the communication transceiver module is used to communicate with the satellite service computer of the simulated satellite to receive the thrust value calculated by the satellite service, and send the thrust value to the micro-propulsion control component, so that the micro-propulsion control component determines the corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output airflow within the nozzle switching time through the solenoid valve, so as to provide the ground air-floating satellite simulator with thrust corresponding to the thrust value.

2. The micro-propulsion system for a ground-based air-floating satellite simulator according to claim 1, characterized in that: The micro-propulsion control assembly includes: a microcontroller, wherein an input end of the microcontroller is connected to the communication transceiver module, configured to receive the thrust value calculated by the satellite service through the communication transceiver module, determine a corresponding nozzle switching time based on the thrust value, and output a corresponding control signal based on the nozzle switching time; An optocoupler relay, wherein an input end of the optocoupler relay is connected to the microcontroller, the optocoupler relay is used to receive a control signal from the microcontroller, and when the control signal is high, the optocoupler relay outputs a high level; MOS tube, wherein the gate of the MOS tube is connected to the output end of the optocoupler relay, and when the optocoupler relay outputs a high level, the source and drain of the MOS tube are connected to control the solenoid valve to open.

3. The micro-propulsion system for a ground-based air-floating satellite simulator according to claim 2, characterized in that: The micro-propulsion control component further includes a diode and an output resistor forming an output loop with the source and drain of the MOS tube; Wherein, when the source and drain of the MOS tube are not conducting, the voltage across the output resistor is equal to the cut-off voltage of the diode, so that the solenoid valve does not open; When the source and drain of the MOS transistor are turned on, a voltage drop of a high-level target voltage is formed across the output resistor, causing the solenoid valve to open.

4. The micro-propulsion system for a ground-based air-floating satellite simulator according to any one of claims 1 to 3, characterized in that: Also includes: High-pressure gas tank, wherein the high-pressure gas tank is used to store high-pressure gas; A pressure reducing valve, wherein the pressure reducing valve is connected to the high-pressure gas tank and the gas nozzle respectively, and the pressure reducing valve is used to reduce the pressure of the airflow output from the high-pressure gas tank and then output it to the gas nozzle.

5. A method for forming a micro-propulsion system, characterized in that: The method for forming the micro-propulsion system is used to form the micro-propulsion system for a ground-based air-floating satellite simulator according to any one of claims 1 to 4, wherein the method for forming the micro-propulsion system comprises: Determining a gas nozzle, wherein the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle is used to output airflow to propel the ground-based air-floating satellite simulator to move; Determine a solenoid valve and set the solenoid valve in conjunction with the gas nozzle, wherein the solenoid valve is used to control whether the gas nozzle outputs airflow to propel the ground-based air-floating satellite simulator to move; Determining a micro-propulsion control component and connecting an output end of the micro-propulsion control component to the solenoid valve, wherein the micro-propulsion control component is used to control whether the solenoid valve is open to control whether the gas nozzle outputs airflow; A communication transceiver module is determined, and an output end of the communication transceiver module is connected to an input end of the micro-propulsion control assembly, wherein the communication transceiver module is used to communicate with a satellite service computer of the simulated satellite to receive a thrust value calculated by the satellite service computer, and send the thrust value to the micro-propulsion control assembly, so that the micro-propulsion control assembly determines a corresponding nozzle switching time based on the thrust value, thereby controlling the gas nozzle to output an airflow within the nozzle switching time through the solenoid valve, thereby providing a thrust corresponding to the thrust value to the ground air-bearing satellite simulator.

6. The method for forming a micro-propulsion system according to claim 5, wherein: The step of determining the gas nozzle comprises: In response to a target operation, determining an inlet pressure, a convergence angle, and a divergence angle of the gas nozzle, wherein the target operation includes a pressure configuration operation performed by a target user; determining a throat area of ​​a gas nozzle based on the inlet pressure; Based on the throat area, the convergence angle and the divergence angle, a gas nozzle is determined, wherein the gas nozzle includes a structure belonging to a Laval nozzle, and the Laval nozzle includes three parts: a convergence zone, a throat and a divergence zone. When the gas enters the convergence zone of the Laval nozzle, the area of ​​the nozzle cross section gradually decreases, and when it reaches the throat, the area of ​​the nozzle cross section reaches the minimum. During this process, the gas is continuously accelerated, and the flow rate reaches the maximum when it reaches the throat. After passing through the throat, the gas enters the divergence zone, the area of ​​the nozzle cross section gradually increases, and the flow rate gradually increases.

7. The method for forming a micro-propulsion system according to claim 6, wherein: The step of determining the throat area of ​​the gas nozzle based on the inlet pressure includes: Determine the Mach number at the outlet of the gas nozzle based on the inlet pressure of the gas nozzle, the ambient pressure and the air heat ratio; determining an outlet cross-sectional temperature of the gas nozzle based on the inlet temperature of the gas nozzle, the air heat ratio, and the outlet Mach number; determining a sound velocity at an outlet section of a gas nozzle based on an air gas constant, the air heat ratio, and the outlet section temperature; determining an outlet gas velocity based on the outlet Mach number and the outlet cross-sectional sound velocity; determining a flow mass ratio based on a target thrust and an outlet gas velocity, wherein the target thrust is achieved in response to the target operation; determining an outlet area based on the flow mass ratio, the air gas constant, the outlet cross-sectional temperature, the outlet gas velocity, and the ambient pressure, wherein the outlet area has a positive correlation with the flow mass ratio, the air gas constant, and the outlet cross-sectional temperature, and has a negative correlation with the outlet area and the outlet gas velocity and the ambient pressure; A throat area is determined based on the outlet area, the outlet Mach number, and the air heat ratio.

8. The method for forming a micro-propulsion system according to claim 7, wherein: The step of determining the outlet Mach number of the gas nozzle based on the inlet pressure of the gas nozzle, the ambient pressure and the air heat ratio comprises: determining a ratio between an inlet pressure of a gas nozzle and an ambient pressure to obtain a first ratio, and determining a difference between the air heat ratio and a first parameter to obtain a first difference; determining a ratio between a second parameter and the first difference to obtain a second ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; determining a ratio between the first difference and the air heat ratio to obtain a third ratio, and performing a power operation on the first ratio based on the third ratio to obtain a first power operation result; determining a difference between the first power operation result and the first parameter to obtain a second difference; An outlet Mach number of the gas nozzle is determined based on the second ratio and the second difference, wherein the outlet Mach number has a positive correlation with both the second ratio and the second difference.

9. The method for forming a micro-propulsion system according to claim 7, wherein: The step of determining the outlet cross-sectional temperature of the gas nozzle based on the inlet temperature of the gas nozzle, the air heat ratio and the outlet Mach number comprises: determining a difference between the air heat ratio and a first parameter to obtain a first difference; determining a ratio between the first difference and a second parameter to obtain a fourth ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; performing a power operation on the outlet Mach number based on the second parameter to obtain a second power operation result, and determining a product between the fourth ratio and the second power operation result, and determining a sum of the first parameter and the product; The ratio between the inlet temperature of the gas nozzle and the sum is determined to obtain the outlet cross-sectional temperature.

10. The method for forming a micro-propulsion system according to claim 7, wherein: The step of determining the throat area based on the outlet area, the outlet Mach number and the air heat ratio comprises: Determining a difference between the air heat ratio and a first parameter to obtain a first difference, and determining a sum between the air heat ratio and the first parameter to obtain a first sum; determining a ratio between the first difference and the first sum to obtain a fifth ratio; determining a ratio between the first difference and a second parameter to obtain a sixth ratio, and determining a ratio between the first sum and the second parameter to obtain a seventh ratio, wherein when the first parameter is equal to 1, the second parameter is equal to 2; performing a power operation on the outlet Mach number based on the second parameter to obtain a second power operation result, determining a product between the sixth ratio and the second power operation result, and determining a sum between the first parameter and the product to obtain a second sum; determining a ratio between the second sum and the seventh ratio to obtain an eighth ratio, and performing a power operation on the eighth ratio based on the fifth ratio to obtain a third power operation result; The throat area is determined based on the outlet area, the outlet Mach number, and the result of the third power operation, wherein the throat area has a positive correlation with the outlet area, the outlet Mach number, and the result of the third power operation.

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