Thermal control design method for attitude and orbit control power system

Abstract

The invention provides a thermal control design method of an attitude and orbit control power system, and belongs to the technical field of thermal control design of aerospace attitude and orbit control power systems. Firstly, thermal control requirements of the attitude and orbit control power system are analyzed, a thermal analysis model of the attitude and orbit control power system is designed and simplified, and then initial temperature, space low temperature, a vacuum environment, ascending section space radiation before orbit injection and temperature response of the attitude and orbit control power system when an orbit injection engine works are analyzed; thermal control design and thermal control scheme analysis are conducted on the attitude and orbit control power system, when the temperature does not meet the requirement, the thermal control design scheme is iteratively designed again, and the temperature response of the attitude and orbit control power system is analyzed till the thermal control design scheme, meeting the requirement, of the attitude and orbit control power system is obtained. According to the invention, the speed of the thermal control design method of the attitude and orbit control power system is effectively improved; the thermal control design weight of the attitude and orbit control power system is effectively reduced; and the temperature control precision of the thermal control design of the attitude and orbit control power system is effectively improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermal control design of aerospace attitude and orbit control power system, and in particular relates to a thermal control design method of an attitude and orbit control power system. Background Art

[0002] When the attitude and orbit control power system is working, there is no set orbit and launch time as boundary conditions, and the external environment is relatively harsh. In addition, the attitude and orbit control power system model is relatively complex, covering a variety of single machines and pipelines, and the design of the currently commonly used thermal analysis model is relatively complex. The attitude and orbit control power system has many working sequences, covering a variety of flight sequences and flight conditions, and the space environment is relatively complex. The additional weight of thermal control is controlled within a certain range, and the weight requirements are relatively strict. Existing technology can perform thermal control design for attitude and orbit control power systems, but the temperature control accuracy is poor, the thermal control weight is large, and the model is complex and the design efficiency is low, which cannot meet the design requirements of high precision and low weight of the thermal control solution of the attitude and orbit control power system.

[0003] According to the different characteristics of various units, pipelines and thrusters in the attitude and orbit control power system, the required temperature range is different, and it may also be different in different operating stages. Temperature is an important environmental condition of the attitude and orbit control power system, which affects the operation of the attitude and orbit control power system. Each product in the attitude and orbit control power system maintains its performance within a certain temperature range. In order to adapt to the working temperature conditions, the attitude and orbit control power system needs to control the temperature according to its own characteristics or by using some methods.

[0004] With the continuous development of aerospace technology, the traditional thermal control design method of attitude and orbit control power system is slow, has poor temperature control accuracy and large control weight. In order to make the thermal balance of the overall heat exchange process of the attitude and orbit control power system within the working range and ensure the efficient working state and high reliability working life of the attitude and orbit control power system, a fast and accurate thermal control design method for attitude and orbit control power system has become an urgent need. Summary of the invention

[0005] The technical problem solved by the present invention is to provide a thermal control design method for an attitude and orbit control power system, which solves the problems of slow speed, poor temperature control accuracy and large control weight of traditional thermal control design methods for attitude and orbit control power systems.

[0006] The technical solution adopted by the present invention is: A thermal control design method for an attitude and orbit control power system, comprising the following steps: Step 1: Analyze the thermal control requirements of the attitude and orbit control power system based on the design input; Step 1.1: Analyze the temperature control requirements of the gas cylinders of the attitude and orbit control power system during each flight phase; Step 1.2: Analyze the temperature control requirements of the tank during each flight phase of the attitude and orbit control power system; Step 1.3: Analyze the temperature control requirements of the gas pipelines of the attitude and orbit control power system during each flight phase; Step 1.4: Analyze the temperature control requirements of the propellant lines of the attitude and orbit control power system during each flight phase; Step 1.5: Analyze the temperature control requirements of the thrusters of the attitude and orbit control power system during each flight phase; Step 2: Design a thermal analysis model of the attitude and orbit control power system, draw the 3D model of the attitude and orbit control power system in Creo 3D software, and obtain the thermal analysis model of the attitude and orbit control power system; Step 3: Simplify the thermal analysis model of the attitude and orbit control power system; Step 3.1: In Creo 3D software, export the attitude and orbit control power system thermal analysis model into stp format; Step 3.2: Import the exported stp format file into UG 3D software for processing; Step 3.3: Remove the accessories used to fix the gas pipeline, the propellant pipeline and the single machine, wherein the single machine includes the gas cylinder, the tank and the thruster, and obtain the simplified model of thermal analysis of the attitude and orbit control power system; Step 4: Use the simplified thermal analysis model of the attitude and orbit control power system to conduct space environment analysis on the attitude and orbit control power system; Step 4.1: Initial temperature stage: when the attitude and orbit control power system is launched, the entire system is in the initial environment with a temperature of 25°C. The temperature response of the attitude and orbit control power system is analyzed to obtain the influence of the initial temperature on the temperature of the attitude and orbit control power system. Step 4.2: In the space low temperature stage, when the temperature reaches 4K, analyze the temperature response of the attitude and orbit control power system to obtain the influence of the space low temperature on the temperature of the attitude and orbit control power system; Step 4.3: Vacuum environment stage, i.e., the working altitude of the attitude and orbit control power system reaches a vacuum environment, the temperature response of the attitude and orbit control power system is analyzed, and the influence of the vacuum environment on the temperature of the attitude and orbit control power system is obtained; Step 4.4: Analyze the space radiation of the attitude and orbit control power system during the ascent before orbit entry, and the temperature response of the attitude and orbit control power system when it is affected by the direct solar heat flux, the earth's reflected heat flux, and the earth's infrared heat flux, and obtain the influence of the space radiation of the ascent before orbit entry on the temperature of the attitude and orbit control power system; Step 4.5: Analyze the thruster operation when the attitude and orbit control power system enters orbit, analyze the impact of high temperature radiation caused by the thruster operation on the attitude and orbit control power system, and obtain the impact relationship of the orbit entry engine operation on the temperature of the attitude and orbit control power system; Step 5: Thermal control design of attitude and orbit control power system; Step 5.1: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, thermal control design is performed on the gas cylinder of the attitude and orbit control power system; Step 5.2: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, perform thermal control design on the tank of the attitude and orbit control power system; Step 5.3: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, perform thermal control design on the gas pipeline of the attitude and orbit control power system; Step 5.4: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, thermal control design is performed on the propellant pipeline of the attitude and orbit control power system; Step 5.5: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, thermal control design is performed on the thrusters of the attitude and orbit control power system; Step 5.6: Calculate the total weight of the thermal control design scheme from Step 5.1 to Step 5.5 of the attitude and orbit control power system; Step 6: Analysis of thermal control scheme of attitude and orbit control power system; Step 6.1: Analyze the thermal control design of the gas cylinders, tanks, gas pipelines, propellant pipelines and thrusters in the attitude and orbit control power system, and obtain a thermal control design scheme that meets the requirements based on the analysis results; Step 6.2: Based on the thermal control design scheme obtained in step 6.1, analyze the temperature field of the outer surfaces of the multi-layer insulation components of the attitude and orbit control power system gas cylinders, tanks, gas pipelines, propellant pipelines and thrusters under different flight conditions; Step 6.3: According to the thermal control design scheme obtained in step 6.1, analyze the temperature field of the attitude and orbit control power system gas cylinder, tank, gas pipeline, propellant pipeline and thruster body under different flight conditions; Step 7: Optimize and iterate the thermal control design of the attitude and orbit control power system; Step 7.1: Analyze the temperature field data of each body obtained in step 6.3. The temperature meets the thermal control requirements, and obtain the thermal control design scheme of the attitude and orbit control power system; Step 7.2: Analyze the temperature field data of each body obtained in step 6.3. If the temperature does not meet the thermal control requirements, return to step 5 to design the thermal control scheme for the attitude and orbit control power system.

[0007] Preferably, the accessories used for fixing in step 3.3 include clamps, straps, spacers, screws and nuts.

[0008] Preferably, the thermal control design of the gas cylinder described in step 5.1 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the gas cylinder from the radiation heat exchange of the external environment, and to use an active thermal control method of attaching a series heating plate at one end of the gas cylinder to provide the heat required to maintain the temperature of the gas in the gas cylinder; The thermal control design of the tank described in step 5.2 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the tank and the external environment, and to use an active thermal control method of attaching parallel heating plates at both ends of the tank to provide the heat required to maintain the temperature of the propellant in the tank; The thermal control design of the gas pipeline described in step 5.3 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the gas pipeline and the external environment, and to use an active thermal control method of a spirally wound heating belt to provide the heat required to maintain the temperature of the gas in the gas pipeline; The thermal control design of the propellant pipeline described in step 5.4 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the propellant pipeline and the external environment, and to use an active thermal control method of a spirally wound heating belt to provide the heat required to maintain the temperature of the propellant in the propellant pipeline; The thruster described in step 5.5 includes a solenoid valve and an engine. The thermal control design of the thruster is to use a passive thermal control method of covering the solenoid valve and the engine head with multi-layer insulation components to isolate the thruster from the radiation heat exchange with the external environment. A heat protection box is installed on the combustion chamber of the engine to prevent the high-temperature radiation of the nozzle to the outside world from affecting other components of the attitude and orbit control power system. The heater armor is installed on the solenoid valve and the combustion chamber of the engine to maintain the body temperature of the thruster.

[0009] Preferably, the multi-layer insulation component is formed by arranging a low-temperature multi-layer insulation component, a medium-temperature multi-layer insulation component and a high-temperature multi-layer insulation component in a sequential manner of stacking them layer by layer, and the number of layers is determined according to actual temperature control requirements.

[0010] The beneficial effects of the present invention are: 1. Before the thermal control design of the attitude and orbit control power system, the present invention designs and simplifies the thermal analysis model of the attitude and orbit control power system, analyzes the space environment, accurately analyzes the initial temperature, space low temperature, vacuum environment, space radiation in the ascent phase before entering orbit, and the temperature response of the attitude and orbit control power system when the orbit entry engine is working, and effectively improves the speed of the thermal control design method of the attitude and orbit control power system.

[0011] 2. The present invention adopts a combination of active thermal control and passive thermal control to carry out thermal control design for the attitude and orbit control power system. In passive thermal control, a thermal control method that combines low-temperature multi-layer insulation components, medium-temperature multi-layer insulation components and high-temperature multi-layer insulation components replaces the traditional insulation scheme of a single insulation component. While ensuring the temperature control requirements, the weight of the thermal control design of the attitude and orbit control power system is effectively reduced.

[0012] 3. The present invention adopts a combination of a heat protection box, a heater and a heat insulation component in the thermal control scheme of the thruster part, which prevents the high temperature radiation of the nozzle to the outside from affecting other components of the attitude and orbit control power system, and ensures that the thruster works at the body temperature.

[0013] 4. After the thermal control design of the attitude and orbit control power system, the present invention analyzes the temperature field of the outer surface and the body of the multi-layer thermal insulation component of the attitude and orbit control power system under different flight conditions, optimizes and iterates the thermal control design scheme, obtains an accurate thermal control design scheme, and effectively improves the temperature control accuracy of the thermal control design of the attitude and orbit control power system. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a flow chart of the thermal control design method for the attitude and orbit control power system. DETAILED DESCRIPTION

[0015] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0016] like Figure 1 As shown, the principle of the present invention is: firstly, the thermal control requirements of the attitude and orbit control power system are analyzed, and the thermal analysis model of the attitude and orbit control power system is designed and simplified; then, the temperature response of the attitude and orbit control power system during the initial temperature, space low temperature, vacuum environment, space radiation in the ascent phase before entering orbit, and operation of the orbit entry engine are analyzed; the thermal control design and thermal control scheme analysis of the attitude and orbit control power system are performed; if the temperature meets the requirements, a high-precision and low-weight thermal control scheme is obtained; if the temperature does not meet the requirements, the thermal control scheme is redesigned, and the temperature response of the attitude and orbit control power system is analyzed, until a thermal control design scheme of the attitude and orbit control power system that meets the requirements is obtained, and the design requirements of high-precision and low-weight thermal control of the attitude and orbit control power system are met.

[0017] A thermal control design method for an attitude and orbit control power system, wherein the attitude and orbit control power system is mainly composed of a thruster, a tank, a gas cylinder, valves and pipelines, and includes the following steps: Step 1: Analyze the thermal control requirements of the attitude and orbit control power system based on the design input; Step 1.1: Analyze the temperature control requirements of the gas cylinders of the attitude and orbit control power system during each flight phase; Step 1.2: Analyze the temperature control requirements of the tank during each flight phase of the attitude and orbit control power system; Step 1.3: Analyze the temperature control requirements of the gas pipelines of the attitude and orbit control power system during each flight phase; Step 1.4: Analyze the temperature control requirements of the propellant lines of the attitude and orbit control power system during each flight phase; Step 1.5: Analyze the temperature control requirements of the thrusters of the attitude and orbit control power system during each flight phase; Step 2: Design a thermal analysis model of the attitude and orbit control power system, draw the 3D model of the attitude and orbit control power system in Creo 3D software, and obtain the thermal analysis model of the attitude and orbit control power system; Step 3: Simplify the thermal analysis model of the attitude and orbit control power system; Step 3.1: In Creo 3D software, export the attitude and orbit control power system thermal analysis model into stp format; Step 3.2: Import the exported stp format file into UG 3D software for processing; Step 3.3: Remove the clamps, straps, spacers, screws and nuts used to fix the gas pipelines, propellant pipelines, gas cylinders, tanks and thrusters to obtain a simplified model for thermal analysis of the attitude and orbit control power system; Step 4: Use the simplified thermal analysis model of the attitude and orbit control power system to conduct space environment analysis on the attitude and orbit control power system; Step 4.1: Initial temperature stage: when the attitude and orbit control power system is launched, the entire system is in the initial environment with a temperature of 25°C. The temperature response of the attitude and orbit control power system is analyzed to obtain the influence of the initial temperature on the temperature of the attitude and orbit control power system. Step 4.2: In the space low temperature stage, when the temperature reaches 4K, analyze the temperature response of the attitude and orbit control power system to obtain the influence of the space low temperature on the temperature of the attitude and orbit control power system; Step 4.3: Vacuum environment stage: As the orbit altitude increases, the air pressure value continues to decrease, and the working altitude of the attitude and orbit control power system reaches a vacuum environment. The temperature response of the attitude and orbit control power system is analyzed to obtain the influence of the vacuum environment on the temperature of the attitude and orbit control power system; Step 4.4: Analyze the space radiation of the attitude and orbit control power system during the ascent before orbit entry, and the temperature response of the attitude and orbit control power system when it is affected by the direct solar heat flux, the earth's reflected heat flux, and the earth's infrared heat flux, and obtain the influence of the space radiation of the ascent before orbit entry on the temperature of the attitude and orbit control power system; Step 4.5: Analyze the working of the thrusters when the attitude and orbit control power system enters orbit. When the thrusters are working, high temperatures will continue to be generated. When the thrusters stop working, the high temperature will not suddenly change, and they will continue to exchange heat with the surrounding environment in the form of radiation heat exchange. Analyze the impact of the high temperature radiation brought by the thrusters on the attitude and orbit control power system, and obtain the impact relationship of the orbital engine working on the temperature of the attitude and orbit control power system. Step 5: Thermal control design of attitude and orbit control power system; Step 5.1: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, a thermal control design is performed on the gas cylinder of the attitude and orbit control power system, and a passive thermal control method is used to isolate the gas cylinder from the radiation heat exchange between the gas cylinder and the external environment. Specifically, a multi-layer thermal insulation component is combined into one by arranging a low-temperature multi-layer thermal insulation component, a medium-temperature multi-layer thermal insulation component, and a high-temperature multi-layer thermal insulation component in layers in sequence, and then the multi-layer thermal insulation component is covered on the gas cylinder to achieve the effect of isolating the gas cylinder from the radiation heat exchange between the gas cylinder and the external environment; an active thermal control method of attaching a series heating plate at one end of the gas cylinder is used to provide the gas in the gas cylinder with the heat required to maintain the temperature; Step 5.2: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, a thermal control design is performed on the tank of the attitude and orbit control power system, and a passive thermal control method is used to isolate the tank from the radiation heat exchange between the tank and the external environment. Specifically, a multi-layer thermal insulation component is combined into one by arranging a low-temperature multi-layer thermal insulation component, a medium-temperature multi-layer thermal insulation component, and a high-temperature multi-layer thermal insulation component in layers in sequence, and then the tank is covered with the multi-layer thermal insulation component to achieve the effect of isolating the tank from the radiation heat exchange between the tank and the external environment; an active thermal control method of attaching parallel heating plates at both ends of the tank is used to provide the heat required to maintain the temperature of the propellant in the tank; Step 5.3: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, a thermal control design is performed on the gas pipeline of the attitude and orbit control power system, and a passive thermal control method is used for the gas pipeline to isolate the radiation heat exchange between the gas pipeline and the external environment. Specifically, a multi-layer thermal insulation component is combined into one by arranging a low-temperature multi-layer thermal insulation component, a medium-temperature multi-layer thermal insulation component, and a high-temperature multi-layer thermal insulation component in layers in sequence, and then the gas pipeline is covered with the multi-layer thermal insulation component to achieve the effect of isolating the radiation heat exchange between the gas pipeline and the external environment; an active thermal control method of a spirally wound heating belt is used to provide the heat required to maintain the temperature of the gas in the gas pipeline; Step 5.4: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, a thermal control design is performed on the propellant pipeline of the attitude and orbit control power system, and a passive thermal control method is used to isolate the propellant pipeline from the radiation heat exchange between the propellant pipeline and the external environment. Specifically, a multi-layer thermal insulation component is combined into one by arranging a low-temperature multi-layer thermal insulation component, a medium-temperature multi-layer thermal insulation component, and a high-temperature multi-layer thermal insulation component in layers in sequence, and then the multi-layer thermal insulation component is coated on the propellant pipeline to achieve the effect of isolating the propellant pipeline from the radiation heat exchange between the propellant pipeline and the external environment; an active thermal control method of a spirally wound heating belt is used to provide the heat required to maintain the temperature of the propellant in the propellant pipeline; Step 5.5: According to the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, a thermal control design is performed on the thruster of the attitude and orbit control power system, and a passive thermal control method is used to isolate the thruster from the radiation heat exchange between the thruster and the external environment. The thruster includes a solenoid valve and an engine. Specifically, a multi-layer thermal insulation component is combined into one by arranging a low-temperature multi-layer thermal insulation component, a medium-temperature multi-layer thermal insulation component and a high-temperature multi-layer thermal insulation component in layers in sequence, and then the multi-layer thermal insulation component is coated on the solenoid valve and the engine head to achieve the effect of isolating the thruster from the radiation heat exchange between the thruster and the external environment. A heat protection box is installed outside the combustion chamber of the engine to prevent the high-temperature radiation of the nozzle to the outside from affecting other components of the attitude and orbit control power system. The heater armor is installed on the solenoid valve and the combustion chamber of the engine to maintain the body temperature of the thruster; Step 5.6: Calculate the total weight of the thermal control design scheme from Step 5.1 to Step 5.5 of the attitude and orbit control power system; Step 6: Analysis of thermal control scheme of attitude and orbit control power system; Step 6.1: Analyze the thermal control design of the gas cylinders, tanks, gas pipelines, propellant pipelines and thrusters in the attitude and orbit control power system, and obtain a thermal control design scheme that meets the requirements based on the analysis results; Step 6.2: Based on the thermal control design scheme obtained in step 6.1, analyze the temperature field of the outer surfaces of the multi-layer insulation components of the attitude and orbit control power system gas cylinders, tanks, gas pipelines, propellant pipelines and thrusters under different flight conditions; Step 6.3: According to the thermal control design scheme obtained in step 6.1, analyze the temperature field of the attitude and orbit control power system gas cylinder, tank, gas pipeline, propellant pipeline and thruster body under different flight conditions; Step 7: Optimize and iterate the thermal control design of the attitude and orbit control power system; Step 7.1: Analyze the temperature field data of each body obtained in step 6.3. The temperature meets the thermal control requirements, and obtain the thermal control design scheme of the attitude and orbit control power system; Step 7.2: Analyze the temperature field data of each body obtained in step 6.3. If the temperature does not meet the thermal control requirements, return to step 5 to redesign the thermal control scheme of the attitude and orbit control power system. Verify the temperature field of the outer surface of the multi-layer insulation component and the attitude and orbit control power system body under different flight conditions under the new scheme until a high-precision and low-weight attitude and orbit control power system thermal control design scheme that meets the temperature control requirements is obtained.

[0018] The above are specific embodiments of the present invention and the technical principles used. Any modifications and equivalent changes based on the technical solution of the present invention should be included in the protection scope of the present invention.

Claims

1. A thermal control design method for an attitude and orbit control power system, characterized in that: The following steps are involved: Step 1: Analyze the thermal control requirements of the attitude and orbit control power system based on the design input; Step 1.1: Analyze the temperature control requirements of the gas cylinders of the attitude and orbit control power system during each flight phase; Step 1.2: Analyze the temperature control requirements of the tank during each flight phase of the attitude and orbit control power system; Step 1.3: Analyze the temperature control requirements of the gas pipelines of the attitude and orbit control power system during each flight phase; Step 1.4: Analyze the temperature control requirements of the propellant lines of the attitude and orbit control power system during each flight phase; Step 1.5: Analyze the temperature control requirements of the thrusters of the attitude and orbit control power system during each flight phase; Step 2: Design a thermal analysis model of the attitude and orbit control power system, draw the 3D model of the attitude and orbit control power system in Creo 3D software, and obtain the thermal analysis model of the attitude and orbit control power system; Step 3: Simplify the thermal analysis model of the attitude and orbit control power system; Step 3.1: In Creo 3D software, export the attitude and orbit control power system thermal analysis model into stp format; Step 3.2: Import the exported stp format file into UG 3D software for processing; Step 3.3: Remove the accessories used to fix the gas pipeline, the propellant pipeline and the single machine, wherein the single machine includes the gas cylinder, the tank and the thruster, and obtain the simplified model of thermal analysis of the attitude and orbit control power system; Step 4: Use the simplified thermal analysis model of the attitude and orbit control power system to conduct space environment analysis on the attitude and orbit control power system; Step 4.1: Initial temperature stage: when the attitude and orbit control power system is launched, the entire system is in the initial environment with a temperature of 25°C. The temperature response of the attitude and orbit control power system is analyzed to obtain the influence of the initial temperature on the temperature of the attitude and orbit control power system. Step 4.2: In the space low temperature stage, when the temperature reaches 4K, analyze the temperature response of the attitude and orbit control power system to obtain the influence of the space low temperature on the temperature of the attitude and orbit control power system; Step 4.3: Vacuum environment stage, i.e., the working altitude of the attitude and orbit control power system reaches a vacuum environment, the temperature response of the attitude and orbit control power system is analyzed, and the influence of the vacuum environment on the temperature of the attitude and orbit control power system is obtained; Step 4.4: Analyze the space radiation of the attitude and orbit control power system during the ascent before orbit entry, and the temperature response of the attitude and orbit control power system when it is affected by the direct solar heat flux, the earth's reflected heat flux, and the earth's infrared heat flux, and obtain the influence of the space radiation of the ascent before orbit entry on the temperature of the attitude and orbit control power system; Step 4.5: Analyze the thruster operation when the attitude and orbit control power system enters orbit, analyze the impact of high temperature radiation caused by the thruster operation on the attitude and orbit control power system, and obtain the impact relationship of the orbit entry engine operation on the temperature of the attitude and orbit control power system; Step 5: Thermal control design of attitude and orbit control power system; Step 5.1: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, thermal control design is performed on the gas cylinder of the attitude and orbit control power system; Step 5.2: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, perform thermal control design on the tank of the attitude and orbit control power system; Step 5.3: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, perform thermal control design on the gas pipeline of the attitude and orbit control power system; Step 5.4: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, thermal control design is performed on the propellant pipeline of the attitude and orbit control power system; Step 5.5: Based on the temperature response of the attitude and orbit control power system in the space environment obtained in step 4, thermal control design is performed on the thrusters of the attitude and orbit control power system; Step 5.6: Calculate the total weight of the thermal control design scheme from Step 5.1 to Step 5.5 of the attitude and orbit control power system; Step 6: Analysis of thermal control scheme of attitude and orbit control power system; Step 6.1: Analyze the thermal control design of the gas cylinders, tanks, gas pipelines, propellant pipelines and thrusters in the attitude and orbit control power system, and obtain a thermal control design scheme that meets the requirements based on the analysis results; Step 6.2: Based on the thermal control design scheme obtained in step 6.1, analyze the temperature field of the outer surfaces of the multi-layer insulation components of the attitude and orbit control power system gas cylinders, tanks, gas pipelines, propellant pipelines and thrusters under different flight conditions; Step 6.3: According to the thermal control design scheme obtained in step 6.1, analyze the temperature field of the attitude and orbit control power system gas cylinder, tank, gas pipeline, propellant pipeline and thruster body under different flight conditions; Step 7: Optimize and iterate the thermal control design of the attitude and orbit control power system; Step 7.1: Analyze the temperature field data of each body obtained in step 6.

3. The temperature meets the thermal control requirements, and obtain the thermal control design scheme of the attitude and orbit control power system; Step 7.2: Analyze the temperature field data of each body obtained in step 6.

3. If the temperature does not meet the thermal control requirements, return to step 5 to design the thermal control scheme for the attitude and orbit control power system.

2. The thermal control design method for attitude and orbit control power system according to claim 1, characterized in that: The accessories used for fixing in step 3.3 include clamps, straps, spacers, screws and nuts.

3. The thermal control design method for attitude and orbit control power system according to claim 1, characterized in that: The thermal control design of the gas cylinder described in step 5.1 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the gas cylinder and the external environment, and to use an active thermal control method of attaching a series heating plate at one end of the gas cylinder to provide the heat required to maintain the temperature of the gas in the gas cylinder; The thermal control design of the tank described in step 5.2 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the tank and the external environment, and to use an active thermal control method of attaching parallel heating plates at both ends of the tank to provide the heat required to maintain the temperature of the propellant in the tank; The thermal control design of the gas pipeline described in step 5.3 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the gas pipeline and the external environment, and to use an active thermal control method of a spirally wound heating belt to provide the heat required to maintain the temperature of the gas in the gas pipeline; The thermal control design of the propellant pipeline described in step 5.4 is to use a passive thermal control method of coating a multi-layer thermal insulation component to isolate the radiation heat exchange between the propellant pipeline and the external environment, and to use an active thermal control method of a spirally wound heating belt to provide the heat required to maintain the temperature of the propellant in the propellant pipeline; The thruster described in step 5.5 includes a solenoid valve and an engine. The thermal control design of the thruster is to use a passive thermal control method of covering the solenoid valve and the engine head with multi-layer insulation components to isolate the thruster from the radiation heat exchange with the external environment. A heat protection box is installed on the combustion chamber of the engine to prevent the high-temperature radiation of the nozzle to the outside world from affecting other components of the attitude and orbit control power system. The heater armor is installed on the solenoid valve and the combustion chamber of the engine to maintain the body temperature of the thruster.

4. The thermal control design method for attitude and orbit control power system according to claim 3 is characterized in that: The multi-layer thermal insulation component is formed by arranging a low-temperature multi-layer thermal insulation component, a medium-temperature multi-layer thermal insulation component and a high-temperature multi-layer thermal insulation component in a sequential manner of stacking them layer by layer.

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