A Mars vehicle thermal control system and method

Abstract

The application relates to a Mars spacecraft temperature control system and method, and relates to a temperature control system and method. In order to solve the problem that an existing Mars spacecraft temperature control system cannot guarantee accurate planning and flexible operation of the Mars spacecraft under the condition of limited energy budget, cannot maximize temperature control energy, and cannot meet the corresponding allowable temperature limit of different temperature control modes in a variable temperature control scene, the temperature control system comprises a base station subsystem, a spacecraft subsystem and an operating environment system; the base station subsystem is composed of a first temperature measurement module, a first temperature adjustment module and a base station control module; and the spacecraft subsystem is composed of a second temperature control module, a second temperature adjustment module and a spacecraft control module. The application belongs to the technical field of spacecraft thermal management.

Description

TECHNICAL FIELD

[0001] The present application relates to a temperature control system and method, belonging to the technical field of spacecraft thermal management. BACKGROUND

[0002] Mars is adjacent to the Earth in the solar system and has similar physical volume and topography to the Earth, and Mars exploration has important significance for expanding human living space and exploring the origin of life. Mars spacecraft is positioned as an aerial exploration platform to assist the Mars rover in efficiently completing the assigned task, with extremely wide application prospects, due to its unique high flight speed, large exploration breadth, local exploration capability and pinpoint landing exploration capability. In the traditional spacecraft temperature control scheme, external thermal insulation materials are wrapped, and heat sources are arranged inside to actively generate heat through heat conduction to maintain survival in low-temperature environments, fans or liquid pumps are arranged to actively dissipate heat through forced convection to achieve high-temperature overheat protection, and temperature sensors are installed at specific positions to achieve closed-loop control of the above temperature regulation.

[0003] Small and low-power Mars spacecraft need to store and release the limited energy generated by the solar cell array through secondary batteries, and the spacecraft must be lightweight and energy-saving to achieve energy operation balance. Influenced by the rocket carrying capacity and the thin atmosphere of Mars, the Mars spacecraft has very strict mass, envelope size and power constraints. Influenced by the fine charged dust in the atmosphere of Mars, the Mars spacecraft needs to be sealed, which further reduces the heat dissipation efficiency of the thermal convection of the high-power power device in the thin atmosphere, and the inherent ratio of thermal inertia to exposed area makes it very difficult for the spacecraft to survive and maneuver. Influenced by the extreme day-night temperature difference of Mars, the Mars spacecraft needs to simultaneously consider the survival maintenance at-128℃ in the extreme low temperature at night and the overheat protection at 27℃ during the day. These factors greatly hinder the design of the temperature control system of the Mars spacecraft:

[0004] 1. The energy budget of the temperature control system is limited, and high-fidelity energy consumption modeling and component temperature prediction are needed to allow the Mars spacecraft to make accurate plans and ensure flexible operation;

[0005] 2. The temperature control system works in a low-power mode, and the thermal model of the low-power system has uncertainty;

[0006] 3. The temperature control system works in a harsh environment, and needs to minimize the temperature control energy while meeting the different temperature control mode corresponding allowable temperature limits in the variable temperature control scene. SUMMARY

[0007] The application discloses a Mars spacecraft temperature control system and method.

[0008] The temperature control system comprises a base station subsystem, a spacecraft subsystem and a running environment system.

[0009] Further, the base station auxiliary equipment comprises a base station control component, a first temperature monitoring component, a first temperature adjusting component, a base station wireless communication component and a Mars environment analysis component.

[0010] Further, the spacecraft control device comprises a flight control component, a second temperature adjusting component, a spacecraft wireless communication component and a second temperature monitoring component.

[0011] The temperature control method comprises the following steps:

[0012] Step 1: querying the state of the spacecraft body;

[0013] Step 2: judging whether the state of the spacecraft body is a dormant state, if yes, performing a dormant state Mars spacecraft temperature control scheme, and performing the next step; if not, performing step 3.

[0014] Step 1: Determine if the spacecraft is in standby mode. If so, implement the standby mode Mars spacecraft temperature control scheme and proceed to step 2. If not, proceed to step 3.

[0015] Step 1: Determine if the spacecraft body is in a ready state. If so, implement the ready state Mars spacecraft temperature control scheme and proceed with step 2; otherwise, proceed with step 3.

[0016] The steps are as follows: First, determine whether the spacecraft body is in a working state. If it is, implement the working state Mars spacecraft temperature control scheme and proceed with the steps. If not, proceed with the steps.

[0017] Step 1: Determine if the Mars spacecraft's lifespan has ended; if yes, end the process; otherwise, proceed to step 2.

[0018] Furthermore, the specific steps of the temperature control scheme for the Mars spacecraft in hibernation mode are as follows:

[0019] Step: Control the first life support thermometer to measure the real-time temperature of the life support core components in hibernation mode;

[0020] Step: Control the base station processor to read the real-time temperature of the dormant life support core component and compare it with the first preset life support temperature value;

[0021] Step: Determine whether the real-time temperature of the dormant life support core component is lower than the first life support temperature preset value; if yes, control the first life support heater to be turned on; if no, control the first life support heater to be turned off.

[0022] Step: End.

[0023] Furthermore, the specific steps of the Mars spacecraft temperature control scheme in standby mode are as follows:

[0024] Step: Control the second life support thermometer to continuously measure the real-time temperature of the life support core components in standby mode;

[0025] Step: Control the aircraft processor to read the real-time temperature of the standby life support core component and compare it with the second life support temperature preset value;

[0026] Step: Determine whether the real-time temperature of the standby life support core component is lower than the second life support temperature preset value; if yes, control the second life support heater to be turned on; if no, control the second life support heater to be turned off.

[0027] Step: Control the aircraft processor to package the real-time temperature of the operating state life support core component, the real-time temperature of the operating state overheating component, and the real-time temperature of the operating state underactive component into thermodynamic information of the internal environment of the operating state aircraft body.

[0028] Step: Control the aircraft's wireless communicator to transmit the thermodynamic information of the internal environment of the aircraft body in its working state to the base station wireless communicator.

[0029] Step: Control the base station wireless communicator to receive the operating status thermodynamic information of the internal environment of the aircraft body transmitted by the aircraft wireless communicator;

[0030] Step: Control the Mars environment analyzer to measure the thermodynamic information of the external environment of the spacecraft body in preparation state;

[0031] Step: Control the spacecraft processor to use the preset working plan of the Mars spacecraft, the preset power plan of the underactive component heater, and the thermodynamic information of the external environment of the spacecraft body in the working state as boundary conditions of the thermodynamic model of the spacecraft body to calculate the thermodynamic prediction information of the internal environment of the spacecraft body in the working state.

[0032] Step: Control the aircraft processor to analyze the prediction results of the thermodynamic information of the internal environment of the aircraft body in the working state and the thermodynamic prediction information of the internal environment of the aircraft body in the working state.

[0033] Step: Control the aircraft processor to iteratively correct the aircraft's thermodynamic model based on the prediction results;

[0034] Step: End.

[0035] Furthermore, the specific steps for preparing the temperature control scheme for the Mars spacecraft are as follows:

[0036] Steps: Control the second life support thermometer to measure the initial temperature of the life support core component in the preparation state; control the second life support thermometer to measure the real-time temperature of the life support core component in the preparation state; control the underactivated component thermometer to measure the initial temperature of the underactivated component in the preparation state; control the overheating component thermometer to measure the initial temperature of the overheating component in the preparation state.

[0037] Step: Control the aircraft processor to read the real-time temperature of the life support core component in the preparation state and compare it with the third life support temperature preset value;

[0038] Step: Determine whether the real-time temperature of the life support core component in the preparation state is lower than the third life support temperature preset value; if yes, control the second life support heater to be in the on state; if no, control the second life support heater to be in the off state.

[0039] Steps: Control the aircraft processor to read the starting temperature of the life support core component in the preparation state, the starting temperature of the overheating component in the preparation state, and the starting temperature of the underactive component in the preparation state, and package them into the thermodynamic information of the internal environment of the aircraft body in the preparation state; control the aircraft wireless communicator to transmit the thermodynamic information of the internal environment of the aircraft body in the preparation state to the base station wireless communicator.

[0040] Step: Control the base station wireless communicator to receive the thermodynamic information of the internal environment of the aircraft body in the preparation state transmitted by the aircraft wireless communicator.

[0041] Step: Control the Mars environment analyzer to measure and store the thermodynamic information of the external environment of the spacecraft body in the preparation state;

[0042] Step: Control the base station processor to use the Mars spacecraft mission target, the thermodynamic information of the external environment of the spacecraft in the preparation state, the thermodynamic information of the internal environment of the spacecraft in the preparation state, the preset activation temperature of the underheating activation component, the preset overheating temperature of the overheating component, and the preset fourth-dimensional temperature as boundary conditions of the spacecraft's thermodynamic model to calculate and store the preset working plan of the Mars spacecraft and the preset power plan of the underheating component heater;

[0043] Step: Control the base station wireless communicator to transmit the preset working plan of the Mars spacecraft and the preset power plan of the underactive component heater to the spacecraft wireless communicator;

[0044] Step: Control the spacecraft's wireless communicator to receive and store the preset operating plan of the Mars spacecraft and the preset power plan of the underactive component heater transmitted by the base station's wireless communicator;

[0045] Step: Control the aircraft processor to read the preset power plan of the underactive component heater, and control the power of the underactive component heater accordingly;

[0046] Step: End.

[0047] Furthermore, the specific steps of the Mars spacecraft temperature control scheme during operation are as follows:

[0048] Steps: Control the second life support thermometer to continuously measure the real-time temperature of the life support core component in the working state; control the underactivated component thermometer to continuously measure the real-time temperature of the underactivated component in the working state; control the overheating component thermometer to continuously measure the real-time temperature of the overheating component in the working state.

[0049] Step: Control the spacecraft processor to read and execute the preset work plan of the Mars spacecraft;

[0050] Step: Control the aircraft processor to read the real-time temperature of the operating state life support core component and compare it with the third life support temperature preset value;

[0051] Step: Determine whether the real-time temperature of the life support core component in the working state is less than the third life support temperature preset value; if yes, control the second life support heater to be in the on state; if no, control the second life support heater to be in the off state.

[0052] Steps: Control the aircraft processor to read and store the real-time temperature of the life support core component in the working state; control the aircraft processor to read and store the real-time temperature of the underactive component in the working state; control the aircraft processor to read and store the real-time temperature of the overheating component in the working state.

[0053] Steps: Control the base station processor to read and execute the preset work plan of the Mars spacecraft; control the Mars environment analyzer to measure and store the thermodynamic information of the external environment of the Mars spacecraft under working conditions;

[0054] Step: End.

[0055] The beneficial effects of this invention are:

[0056] 1. Given the limited energy budget of the temperature control system, high-fidelity energy consumption modeling and component temperature prediction are obtained through iterative correction to allow the aircraft to make precise plans and ensure flexible operation;

[0057] 2. Under the premise that the temperature control system is operating in low-power mode, the accuracy of the low-power system thermal model is improved by simultaneously establishing a thermal model of the Mars working environment and reducing the number of temperature control nodes of the Mars equipment.

[0058] 3. Under harsh operating conditions of the temperature control system, the energy required for temperature control is minimized by differentiating aircraft modules with different limitations, while simultaneously meeting the allowable temperature limits for different temperature control modes in variable temperature control scenarios. Attached Figure Description

[0059] Figure 1 This is a functional block diagram of the present invention;

[0060] Figure 2 This is a functional module diagram of the operating environment of the Mars spacecraft's temperature control system;

[0061] Figure 3 This is a schematic diagram of a Mars spacecraft using a temperature control system.

[0062] Figure 4 This is a flowchart of the temperature control method for Mars spacecraft;

[0063] Figure 5 This is a flowchart of the temperature control scheme for a Mars spacecraft in hibernation mode;

[0064] Figure 6 This is a flowchart of the temperature control scheme for the Mars spacecraft in standby mode;

[0065] Figure 7 This is a flowchart of the temperature control scheme for the Mars spacecraft in preparation state;

[0066] Figure 8 This is a flowchart of the temperature control scheme for the Mars spacecraft in its operational state. Detailed Implementation

[0067] Specific implementation method one: Combining Figures 1 to 3 This embodiment describes a Mars spacecraft temperature control system comprising a base station subsystem S110, a spacecraft subsystem S120, and an operating environment system. The base station subsystem S110 consists of a first temperature measurement module S111, a first temperature adjustment module S112, and a base station control module S113. The spacecraft subsystem S120 consists of a second temperature control module S121, a second temperature adjustment module S122, and a spacecraft control module S123. The operating environment system includes base station auxiliary equipment 100 and spacecraft control equipment 200. The first temperature measurement module S111, the first temperature adjustment module S112, and the base station control module S113 are mutually communicable system modules within the base station subsystem S110, and the second temperature measurement module S121, the second temperature adjustment module S122, and the spacecraft control module S123 are mutually communicable system modules within the spacecraft subsystem S120.

[0068] The Mars spacecraft E100 targeted by the temperature control system described in this invention includes a spacecraft base station E120 and a spacecraft body E110. The spacecraft body E110 includes a life support core component E111, an underactivated component E112, and an overheating component E113. Thermal isolation exists between the life support core component E111, the underactivated component E112, and the overheating component E113.

[0069] When the aircraft body E110 is in the hibernation state, the first temperature measurement module S111 is used to control the first life support thermometer 112 to measure the real-time temperature of the life support core components in the hibernation state and transmit it to the base station management module S113.

[0070] When the aircraft body E110 is in the hibernation state, the base station control module S113 is used to read the real-time temperature of the life support core component in the hibernation state, compare it with the first life support temperature preset value, and transmit the comparison result to the first temperature control module S112.

[0071] When the aircraft body E110 is in the hibernation state, the first temperature control module S112 is used to control the first life support heater 131 to be turned on when the real-time temperature of the life support core component in the hibernation state is lower than the first life support temperature preset value; and to control the first life support heater 131 to be turned off when the real-time temperature of the life support core component in the hibernation state is higher than the first life support temperature preset value.

[0072] When the aircraft body E110 is in the preparation state, the second temperature measurement module S121 is used to control the second life support thermometer 241 to measure the initial temperature of the life support core component in the preparation state and transmit it to the aircraft control module S123; and is also used to control the second life support thermometer 241 to measure the real-time temperature of the life support core component in the preparation state and transmit it to the aircraft control module S123; and is also used to control the underactive component thermometer 242 to measure the initial temperature of the underactive component in the preparation state and transmit it to the aircraft control module S123; and is also used to control the overheating component thermometer 243 to measure the initial temperature of the overheating component in the preparation state and transmit it to the aircraft control module S123.

[0073] When the aircraft body E110 is in the preparation state, the aircraft control module S123 is used to read the real-time temperature of the life support core component in the preparation state, compare it with the third life support temperature preset value, and transmit the comparison result to the second temperature control module S122; and is used to read the initial temperature of the life support core component in the preparation state, the initial temperature of the underactive component in the preparation state, and the initial temperature of the overheating component in the preparation state and package them into the internal environment thermodynamic information of the aircraft body in the preparation state; and is used to control the aircraft wireless communicator 231 to transmit the internal environment thermodynamic information of the aircraft body in the preparation state to the base station wireless communicator 141.

[0074] When the spacecraft body E110 is in the ready state, the base station control module S113 is used to control the Mars environment analyzer 151 to measure and store the external environment thermodynamic information of the spacecraft body in the ready state; and to control the base station wireless communicator 141 to receive the internal environment thermodynamic information of the spacecraft body in the ready state transmitted by the spacecraft wireless communicator 231; and to use the Mars spacecraft mission target, the external environment thermodynamic information of the spacecraft body in the ready state, the internal environment thermodynamic information of the spacecraft body in the ready state, the preset activation temperature of the underheating activation component, the preset overheating temperature of the overheating component, and the preset fourth-dimensional temperature as boundary conditions of the spacecraft body thermodynamic model to calculate and store the preset working plan of the Mars spacecraft and the preset power plan of the underheating component heater; and to control the base station wireless communicator 141 to transmit the preset working plan of the Mars spacecraft and the preset power plan of the underheating component heater to the spacecraft wireless communicator 231.

[0075] When the spacecraft body E110 is in the preparation state, the spacecraft control module S123 is used to control the spacecraft wireless communicator 231 to receive and store the Mars spacecraft preset working plan and the underactive component heater preset power plan transmitted by the base station wireless communicator 141; and is used to read the underactive component heater preset power plan and transmit it to the second temperature control module S122.

[0076] When the aircraft body E110 is in the preparation state, the second temperature control module S122 is used to control the second life support heater 221 to be turned on when the temperature of the life support core component in the preparation state is lower than the third life support temperature preset value; and to control the second life support heater 221 to be turned off when the temperature of the life support core component in the preparation state is higher than the third life support temperature preset value; and to control the power of the underactivated component heater 242 according to the preset power plan of the underactivated component heater.

[0077] When the aircraft body E110 is in the working state, the second temperature measurement module S121 is used to control the second life support thermometer 241 to measure the real-time temperature of the life support core components in the working state and transmit it to the aircraft control module S123; and is used to control the underactive component thermometer 242 to measure the real-time temperature of the underactive components in the working state and transmit it to the aircraft control module S123; and is used to control the overheating component thermometer 243 to measure the real-time temperature of the overheating components in the working state and transmit it to the aircraft control module S123.

[0078] When the spacecraft body E110 is in the working state, the spacecraft control module S123 is used to read and execute the preset working plan of the Mars spacecraft; and to read the real-time temperature of the life support core components in the working state, compare it with the third preset life support temperature value, and transmit it to the second temperature control module S122; and to read and store the real-time temperature of the life support core components in the working state; and to read and store the real-time temperature of the underactive components in the working state; and to read and store the real-time temperature of the overheating components in the working state.

[0079] When the spacecraft body E110 is in the working state, the base station control module S113 is used to read and execute the preset working plan of the Mars spacecraft; and to control the Mars environment analyzer 151 to measure and store the thermodynamic information of the external environment of the spacecraft body in the working state.

[0080] When the aircraft body E110 is in the working state, the second temperature control module S122 is used to control the second life support heater 221 to be turned on when the real-time temperature of the life support core component in the working state is lower than the third life support temperature preset value; and is also used to control the second life support heater 221 to be turned on when the temperature of the life support core component in the working state is lower than the third life support temperature preset value.

[0081] When the aircraft body E110 is in the standby state, the second temperature measurement module is used to control the second life support thermometer 241 to measure the real-time temperature of the life support core components in the standby state and transmit it to the aircraft control module S123.

[0082] When the aircraft body E110 is in the standby state, the aircraft control module S123 is used to read the real-time temperature of the standby life support core component, compare it with the second life support temperature preset value, and transmit the comparison result to the second temperature control module S122; and is used to package the real-time temperature of the operating life support core component, the real-time temperature of the operating overheating component, and the real-time temperature of the operating underactive component into the thermodynamic information of the internal environment of the aircraft body in the operating state; and is used to control the aircraft wireless communicator 231 to transmit the thermodynamic information of the internal environment of the aircraft body in the operating state to the base station wireless communicator 141.

[0083] When the spacecraft body E110 is in the standby state, the base station management module S113 is used to control the base station wireless communicator 141 to receive the thermodynamic information of the internal environment of the spacecraft body in the working state transmitted by the spacecraft wireless communicator 231; and is used to calculate the thermodynamic prediction information of the internal environment of the spacecraft body in the working state by using the preset working plan of the Mars spacecraft, the preset power plan of the underactive component heater, and the thermodynamic information of the external environment of the spacecraft body in the working state as boundary conditions of the spacecraft body thermodynamic model; and is used to analyze the prediction results of the thermodynamic information of the internal environment of the spacecraft body in the working state and the thermodynamic prediction information of the internal environment of the spacecraft body in the working state; and is used to iteratively correct the thermodynamic model of the spacecraft body based on the prediction result analysis.

[0084] When the aircraft body E110 is in the standby state, the second temperature control module S122 is used to control the second life support heater 221 to be turned on when the temperature of the life support core component in the standby state is lower than the second life support temperature preset value; and is used to control the second life support heater 221 to be turned off when the temperature of the life support core component in the standby state is higher than the second life support temperature preset value.

[0085] Specific Implementation Method Two: Combining Figures 1 to 3 This embodiment describes a base station auxiliary device 100 for a Mars spacecraft temperature control system, comprising a base station control component 110, a first temperature monitoring component 120, a first temperature regulating component 130, a base station wireless communication component 140, and a Mars environment analysis component 150. The Mars environment analysis component 150 consists of a Mars environment analyzer 151, the base station wireless communication component 140 consists of a base station wireless communicator 141, the first temperature monitoring component 120 consists of a first life-sustaining thermometer 121, the first temperature regulating component 130 consists of a first life-sustaining heater 131, and the base station control component 110 consists of a base station processor 111, a first temperature controller 112, and a first temperature regulating controller 113. The base station processor 111 stores Mars spacecraft mission objectives, a first life-sustaining temperature preset value, a fourth life-sustaining temperature preset value, an underactivated component activation temperature preset value, an overheating component overheating temperature preset value, and a thermodynamic model of the spacecraft body.

[0086] In this embodiment, the preset activation temperature of the underactivated component is -55℃, and the preset overheating temperature of the overheating component is +120℃.

[0087] Specific implementation method three: Combining Figures 1 to 3This embodiment describes a Mars spacecraft temperature control system with a spacecraft management device 200, comprising a flight control component 210, a second temperature regulation component 220, a spacecraft wireless communication component 230, and a second temperature monitoring component 240. The spacecraft control component 210 consists of a spacecraft processor 211, a second temperature controller 212, and a second temperature control controller 213. The second temperature regulation component 220 consists of a second life-sustaining heater 221, an underactivated component heater 222, and an overheating component thermal inertia device 223. The spacecraft wireless communication component 230 consists of a spacecraft wireless communicator 231. The second temperature monitoring component 240 consists of a second life-sustaining thermometer 241, an underactivated component thermometer 242, and an overheating component thermometer 243.

[0088] The first life-sustaining thermometer 121, the second life-sustaining thermometer 241, the underactive component thermometer 242, and the overheating component thermometer 243 are all made of lightweight temperature sensors, such as RTDs, which are space-appropriate, corrosion-resistant, and have a wide detection range (including -135 to 135°C).

[0089] The first life heater 131 and the second life heater 221 are made of heaters with low weight, high power and the ability to heat a large area, such as PI film heaters.

[0090] The underactive component heater 222 is made of a heater that can be directly integrated into the PCB, has a controllable duty cycle, and stable output power, such as a winding heater.

[0091] The overheating component thermal inertia 223 is made of a high specific heat material, such as aluminum-beryllium alloy or phase change material Octacosane.

[0092] The aircraft processor 211 stores a second life-saving temperature preset value and a third life-saving temperature preset value.

[0093] The first life-sustaining temperature preset value is less than the second life-sustaining temperature preset value, the second life-sustaining temperature preset value is less than the third life-sustaining temperature preset value, and the third life-sustaining temperature preset value is less than the fourth life-sustaining temperature preset value.

[0094] The first life support temperature preset value is the optimal temperature of the life support core component in dormant state, the second life support temperature preset value is the optimal temperature of the life support core component in standby state, the third life support temperature preset value is the optimal temperature of the life support core component in preparation and working states, and the fourth life support temperature preset value is the upper limit temperature of the life support core component in preparation and working states.

[0095] The first life-sustaining temperature preset value is -15℃, the second life-sustaining temperature preset value is +5℃, the third life-sustaining temperature preset value is +10℃, and the first life-sustaining temperature preset value is +40℃.

[0096] The base station control module S123 is a programmable module stored in the base station processor 111 and executable by the base station processor 111. The first temperature measurement module S111 is a programmable module stored in the first temperature measurement controller 112 and executable by the first temperature measurement controller 112. The first temperature adjustment module S112 is a programmable module stored in the first temperature adjustment controller 113 and executable by the first temperature adjustment controller 113. The aircraft control module S123 is a programmable module stored in the aircraft processor 211 and executable by the aircraft station processor 211. The second temperature measurement module S121 is a programmable module stored in the second temperature measurement controller 212 and executable by the second temperature measurement controller 212. The second temperature adjustment module S122 is a programmable module stored in the second temperature adjustment controller 211 and executable by the second temperature controller 211.

[0097] Specific implementation method four: Combination Figure 4 The specific steps of the temperature control method for a Mars spacecraft described in this embodiment are as follows:

[0098] Step S1001: Query the status of the aircraft body E110;

[0099] Step S1002: Determine whether the spacecraft body E110 is in a dormant state. If yes, implement the dormant Mars spacecraft temperature control scheme and proceed to step S1006; otherwise, proceed to step S1003.

[0100] Step S1003: Determine whether the status of the spacecraft body E110 is in standby mode. If yes, implement the standby mode Mars spacecraft temperature control scheme and proceed to step S1006. If no, proceed to step S1004.

[0101] Step S1004: Determine whether the status of the spacecraft body E110 is in the ready state. If yes, implement the ready state Mars spacecraft temperature control scheme and proceed to step S1006; otherwise, proceed to step S1005.

[0102] Step S1005: Determine whether the spacecraft body E110 is in working state. If yes, implement the working state Mars spacecraft temperature control scheme and proceed to step S1006. If no, proceed to step S1006.

[0103] Step S1006: Determine whether the lifespan of this Mars spacecraft E100 has ended; if yes, then end; if no, proceed to step S1001.

[0104] Specific Implementation Method Five: Combining Figure 5 This embodiment describes the specific steps of the temperature control scheme for a dormant Mars spacecraft in step S1002 of the temperature control method described in this embodiment:

[0105] Step S1101: Control the first life support thermometer 121 to measure the real-time temperature of the life support core components in the dormant state;

[0106] Step S1102: Control the base station processor 111 to read the real-time temperature of the dormant life support core component and compare it with the first life support temperature preset value;

[0107] Step S1103: Determine whether the real-time temperature of the dormant life support core component is less than the first life support temperature preset value; if yes, control the first life support heater 121 to be in the on state; if no, control the first life support heater 131 to be in the off state.

[0108] Step S1104: End.

[0109] Specific Implementation Method Six: Combination Figure 6 This embodiment describes the specific steps of the standby state temperature control scheme for a Mars spacecraft in step S1003 of the temperature control method for a Mars spacecraft described in this embodiment:

[0110] Step S1201: Control the second life support thermometer 241 to continuously measure the real-time temperature of the life support core components in standby mode;

[0111] Step S1202: Control the aircraft processor 211 to read the real-time temperature of the standby life support core component and compare it with the second life support temperature preset value;

[0112] Step S1203: Determine whether the real-time temperature of the standby life support core component is less than the second life support temperature preset value; if yes, control the second life support heater 221 to be in the on state; if no, control the second life support heater 221 to be in the off state.

[0113] Step S1204: Control the aircraft processor 211 to package the real-time temperature of the operating state life support core component, the real-time temperature of the operating state overheating component, and the real-time temperature of the operating state underactive component into thermodynamic information of the internal environment of the operating state aircraft body.

[0114] Step S1205: Control the aircraft wireless communicator 231 to transmit the thermodynamic information of the internal environment of the aircraft body in the working state to the base station wireless communicator 141.

[0115] Step S1206: Control the base station wireless communicator 141 to receive the thermodynamic information of the internal environment of the aircraft body in the working state transmitted by the aircraft wireless communicator 231.

[0116] Step S1207: Control the Mars environment analyzer 151 to measure the thermodynamic information of the external environment of the spacecraft body in the preparation state;

[0117] Step S1208: Control the spacecraft processor 210 to use the preset working plan of the Mars spacecraft, the preset power plan of the underactive component heater 222, and the thermodynamic information of the external environment of the working spacecraft body as boundary conditions of the thermodynamic model of the spacecraft body to calculate the thermodynamic prediction information of the internal environment of the working spacecraft body.

[0118] Step S1209: Control the aircraft processor 211 to analyze the prediction results of the thermodynamic information of the internal environment of the aircraft body in the working state and the thermodynamic prediction information of the internal environment of the aircraft body in the working state.

[0119] Step S1210: Control the aircraft processor 211 to iteratively correct the aircraft body thermodynamic model based on the prediction results;

[0120] Step S1211: End.

[0121] Specific implementation method seven: Combination Figure 7 This embodiment describes the specific steps of the Mars spacecraft temperature control scheme in step S1004 of the Mars spacecraft temperature control method as follows:

[0122] Step S1301: Control the second life support thermometer 241 to measure the initial temperature of the life support core component in the preparation state; control the second life support thermometer 241 to measure the real-time temperature of the life support core component in the preparation state; control the underactivated component thermometer 242 to measure the initial temperature of the underactivated component in the preparation state; control the overheating component thermometer 243 to measure the initial temperature of the overheating component in the preparation state.

[0123] Step S1302: Control the aircraft processor 211 to read the real-time temperature of the life support core component in the preparation state and compare it with the third life support temperature preset value;

[0124] Step S1303: Determine whether the real-time temperature of the life support core component in the preparation state is less than the third life support temperature preset value; if yes, control the second life support heater 221 to be in the on state; if no, control the second life support heater 221 to be in the off state.

[0125] Step S1304: Control the aircraft processor 211 to read the starting temperature of the life support core component in the preparation state, the starting temperature of the overheating component in the preparation state, and the starting temperature of the underactive component in the preparation state, and package them into the thermodynamic information of the internal environment of the aircraft body in the preparation state; control the aircraft wireless communicator 231 to transmit the thermodynamic information of the internal environment of the aircraft body in the preparation state to the base station wireless communicator 141.

[0126] Step S1305: Control the base station wireless communicator 141 to receive the thermodynamic information of the internal environment of the aircraft body in the preparation state transmitted by the aircraft wireless communicator 231.

[0127] Step S1306: Control the Mars environment analyzer 151 to measure and store the thermodynamic information of the external environment of the spacecraft body in the preparation state;

[0128] Step S1307: Control the base station processor 111 to use the Mars spacecraft mission target, the thermodynamic information of the external environment of the spacecraft body in the preparation state, the thermodynamic information of the internal environment of the spacecraft body in the preparation state, the preset activation temperature of the underheating activation component, the preset overheating temperature of the overheating component, and the preset fourth generation temperature as boundary conditions of the spacecraft body thermodynamic model to calculate and store the preset working plan of the Mars spacecraft and the preset power plan of the underheating component heater;

[0129] Step S1308: Control the base station wireless communicator 141 to transmit the preset working plan of the Mars spacecraft and the preset power plan of the underactive component heater to the spacecraft wireless communicator 231;

[0130] Step S1309: Control the spacecraft wireless communicator 231 to receive and store the preset working plan of the Mars spacecraft and the preset power plan of the underactive component heater transmitted by the base station wireless communicator 141;

[0131] Step S1310: Control the aircraft processor 211 to read the preset power plan of the underactive component heater, and control the power of the underactive component heater 242 accordingly;

[0132] Step S1311: End.

[0133] Specific implementation method eight: Combination Figure 8This embodiment describes the specific steps of the Mars spacecraft temperature control scheme in step S1005 of the Mars spacecraft temperature control method described in this embodiment, as follows:

[0134] Step S1401: Control the second life support thermometer 241 to continuously measure the real-time temperature of the life support core component in the working state; control the underactivated component thermometer 242 to continuously measure the real-time temperature of the underactivated component in the working state; control the overheating component thermometer 243 to continuously measure the real-time temperature of the overheating component in the working state.

[0135] Step S1402: Control the spacecraft processor 211 to read and execute the preset work plan of the Mars spacecraft;

[0136] Step S1403: Control the aircraft processor 211 to read the real-time temperature of the working state life support core component and compare it with the third life support temperature preset value;

[0137] Step S1404: Determine whether the real-time temperature of the life support core component in the working state is less than the third life support temperature preset value; if yes, control the second life support heater 221 to be in the on state; if no, control the second life support heater 221 to be in the off state.

[0138] Step S1405: Control the aircraft processor 211 to read and store the real-time temperature of the life support core component in the working state; control the aircraft processor 211 to read and store the real-time temperature of the underactive component in the working state; control the aircraft processor 211 to read and store the real-time temperature of the overheating component in the working state.

[0139] Step S1406: Control the base station processor 111 to read and execute the preset work plan of the Mars spacecraft; control the Mars environment analyzer 151 to measure and store the thermodynamic information of the external environment of the Mars spacecraft under working conditions;

[0140] Step S1407: End.

[0141] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent substitutions, and improvements made to the above embodiments without departing from the scope of the present invention, based on the technical essence of the present invention and within the spirit and principles of the present invention, shall still fall within the protection scope of the present invention.

Claims

1. A temperature control method for a Mars spacecraft, wherein the Mars spacecraft temperature control system used therein includes a base station subsystem (S110), a spacecraft subsystem (S120), and an operating environment system; the base station subsystem (S110) consists of a first temperature measurement module (S111), a first temperature adjustment module (S112), and a base station control module (S113); the spacecraft subsystem (S120) consists of a second temperature control module (S121), a second temperature adjustment module (S122), and a spacecraft control module (S123). The system comprises 123), and the operating environment system includes base station auxiliary equipment (100) and aircraft control equipment (200); the first temperature measurement module (S111), the first temperature adjustment module (S112), and the base station control module (S113) are system modules in the base station subsystem (S110) that can communicate with each other; the second temperature control module (S121), the second temperature adjustment module (S122), and the aircraft control module (S123) are system modules in the aircraft subsystem (S120) that can communicate with each other; The base station auxiliary equipment (100) includes a base station control component (110), a first temperature monitoring component (120), a first temperature regulating component (130), a base station wireless communication component (140), and a Mars environment analysis component (150); the Mars environment analysis component (150) is composed of a Mars environment analyzer (151), the base station wireless communication component (140) is composed of a base station wireless communicator (141), the first temperature monitoring component (120) is composed of a first life-saving thermometer (121), the first temperature regulating component (130) is composed of a first life-saving heater (131), the base station control component (110) is composed of a base station processor (111), a first temperature controller (112), and a first temperature control controller (113), the base station processor (111) stores the Mars spacecraft mission objectives, the first life-saving temperature preset value, the fourth life-saving temperature preset value, the underactive component activation temperature preset value, the overheating component overheating temperature preset value, and the spacecraft body thermodynamic model; The aircraft control equipment (200) includes a flight control component (210), a second temperature regulation component (220), an aircraft wireless communication component (230), and a second temperature monitoring component (240); the flight control component (210) consists of an aircraft processor (211), a second temperature controller (212), and a second temperature control controller (213); the second temperature regulation component (220) consists of a second life-sustaining heater (221), an underactivated component heater (222), and an overheat-generating component thermal inertia device (223); the aircraft wireless communication component (230) consists of an aircraft wireless communicator (231); and the second temperature monitoring component (240) consists of a second life-sustaining thermometer (241), an underactivated component thermometer (242), and an overheat-generating component thermometer (243). Its characteristic is that... The specific steps of the method include: Step S1001: Query the status of the aircraft body (E110); Step S1002: Determine whether the spacecraft body (E110) is in a dormant state. If yes, implement the dormant Mars spacecraft temperature control scheme and proceed to step S1006; otherwise, proceed to step S1003. Step S1003: Determine whether the status of the spacecraft body (E110) is in standby mode. If yes, implement the standby mode Mars spacecraft temperature control scheme and proceed to step S1006. If no, proceed to step S1004. The specific steps of the Mars spacecraft's temperature control scheme in standby mode are as follows: Step S1201: Control the second life support thermometer (241) to continuously measure the real-time temperature of the life support core components in standby mode; Step S1202: Control the aircraft processor (211) to read the real-time temperature of the standby life support core component and compare it with the second life support temperature preset value; Step S1203: Determine whether the real-time temperature of the standby life support core component is less than the second life support temperature preset value; if yes, control the second life support heater (221) to be in the on state; if no, control the second life support heater (221) to be in the off state. Step S1204: Control the aircraft processor (211) to package the real-time temperature of the life support core component in standby state, the real-time temperature of the overheating component in standby state, and the real-time temperature of the underactive component in standby state into thermodynamic information of the internal environment of the aircraft body in standby state. Step S1205: Control the aircraft wireless communicator (231) to transmit the thermodynamic information of the internal environment of the aircraft body in standby state to the base station wireless communicator (141). Step S1206: Control the base station wireless communicator (141) to receive the standby state internal environment thermodynamic information of the aircraft body transmitted by the aircraft wireless communicator (231); Step S1207: Control the Mars environment analyzer (151) to measure the thermodynamic information of the external environment of the spacecraft body in the preparation state; Step S1208: Control the flight control component (210) to use the preset working plan of the Mars spacecraft, the preset power plan of the underactive component heater (222), and the thermodynamic information of the external environment of the spacecraft body in standby state as boundary conditions of the thermodynamic model of the spacecraft body to calculate the thermodynamic prediction information of the internal environment of the spacecraft body in standby state. Step S1209: Control the aircraft processor (211) to analyze the prediction results of the thermodynamic information of the internal environment of the aircraft body in the standby state and the thermodynamic prediction information of the internal environment of the aircraft body in the standby state. Step S1210: Control the aircraft processor (211) to iteratively correct the aircraft body thermodynamic model based on the prediction results; Step S1211: End; Step S1004: Determine whether the status of the spacecraft body (E110) is in the ready state. If yes, implement the ready state Mars spacecraft temperature control scheme and proceed to step S1006; otherwise, proceed to step S1005. Step S1005: Determine whether the spacecraft body (E110) is in a working state. If yes, implement the working state Mars spacecraft temperature control scheme and proceed to step S1006. If no, proceed to step S1006. Step S1006: Determine whether the lifespan of this Mars spacecraft (E100) has ended; if yes, then end; if no, proceed to step S1001.

2. The temperature control method for a Mars spacecraft according to claim 1, characterized in that: The specific steps of the temperature control scheme for the Mars spacecraft in hibernation state in step S1002 are as follows: Step S1101: Control the first life support thermometer (121) to measure the real-time temperature of the life support core components in the dormant state; Step S1102: Control the base station processor (111) to read the real-time temperature of the dormant life support core component and compare it with the first life support temperature preset value; Step S1103: Determine whether the real-time temperature of the dormant life support core component is less than the first life support temperature preset value; if yes, control the first life support heater (131) to be in the on state; if no, control the first life support heater (131) to be in the off state. Step S1104: End.

3. The temperature control method for a Mars spacecraft according to claim 1, characterized in that: The specific steps for preparing the temperature control scheme for the Mars spacecraft in step S1004 are as follows: Step S1301: Control the second life support thermometer (241) to measure the initial temperature of the life support core component in the preparation state; control the second life support thermometer (241) to measure the real-time temperature of the life support core component in the preparation state; control the underactivated component thermometer (242) to measure the initial temperature of the underactivated component in the preparation state; control the overheating component thermometer (243) to measure the initial temperature of the overheating component in the preparation state. Step S1302: Control the aircraft processor (211) to read the real-time temperature of the life support core component in the preparation state and compare it with the third life support temperature preset value; Step S1303: Determine whether the real-time temperature of the life support core component in the preparation state is less than the third life support temperature preset value; if yes, control the second life support heater (221) to be in the on state; if no, control the second life support heater (221) to be in the off state. Step S1304: Control the aircraft processor (211) to read the starting temperature of the life support core component in the preparation state, the starting temperature of the overheating component in the preparation state, and the starting temperature of the underactive component in the preparation state, and package them into the thermodynamic information of the internal environment of the aircraft body in the preparation state; control the aircraft wireless communicator (231) to transmit the thermodynamic information of the internal environment of the aircraft body in the preparation state to the base station wireless communicator (141). Step S1305: Control the base station wireless communicator (141) to receive the thermodynamic information of the internal environment of the aircraft body in the preparation state transmitted by the aircraft wireless communicator (231). Step S1306: Control the Mars environment analyzer (151) to measure and store the thermodynamic information of the external environment of the spacecraft body in the preparation state; Step S1307: Control the base station processor (111) to use the Mars spacecraft mission target, the thermodynamic information of the external environment of the spacecraft body in the preparation state, the thermodynamic information of the internal environment of the spacecraft body in the preparation state, the preset activation temperature of the underactivated component, the preset overheating temperature of the overheating component, and the preset fourth generation temperature as boundary conditions of the spacecraft body thermodynamic model to calculate and store the preset working plan of the Mars spacecraft and the preset power plan of the heater of the underactivated component; Step S1308: Control the base station wireless communicator (141) to transmit the preset working plan of the Mars spacecraft and the preset power plan of the underactive component heater to the spacecraft wireless communicator (231). Step S1309: Control the spacecraft wireless communicator (231) to receive and store the preset working plan of the Mars spacecraft and the preset power plan of the underactive component heater transmitted by the base station wireless communicator (141); Step S1310: Control the aircraft processor (211) to read the preset power plan of the underactive component heater, and control the power of the underactive component heater (222) accordingly; Step S1311: End.

4. The temperature control method for a Mars spacecraft according to claim 1, characterized in that: The specific steps of the Mars spacecraft temperature control scheme in step S1005 are as follows: Step S1401: Control the second life support thermometer (241) to continuously measure the real-time temperature of the life support core component in the working state; control the underactivated component thermometer (242) to continuously measure the real-time temperature of the underactivated component in the working state; control the overheating component thermometer (243) to continuously measure the real-time temperature of the overheating component in the working state. Step S1402: Control the spacecraft processor (211) to read and execute the preset work plan of the Mars spacecraft; Step S1403: Control the aircraft processor (211) to read the real-time temperature of the life support core component in the working state and compare it with the third life support temperature preset value; Step S1404: Determine whether the real-time temperature of the life support core component in the working state is less than the third life support temperature preset value; if yes, control the second life support heater (221) to be in the on state; if no, control the second life support heater (221) to be in the off state. Step S1405: Control the aircraft processor (211) to read and store the real-time temperature of the life support core component in the working state; control the aircraft processor (211) to read and store the real-time temperature of the underactive component in the working state; control the aircraft processor (211) to read and store the real-time temperature of the overheating component in the working state; Step S1406: Control the base station processor (111) to read and execute the preset work plan of the Mars spacecraft; control the Mars environment analyzer (151) to measure and store the thermodynamic information of the external environment of the Mars spacecraft in its working state; Step S1407: End.

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