An active and passive integrated thermal control design method for aerospace multifunctional structural batteries

Abstract

The present invention discloses an active and passive integrated thermal control design method for aerospace multifunctional structural batteries, belonging to the field of aerospace thermal control technology. The method first designs distributed active control measures and passive thermal control measures based on multi-stage temperature control according to the configuration, heat consumption parameters and thermophysical property parameters of the multifunctional structural battery; then uses commercial thermal analysis software to establish a thermal analysis model of the multifunctional structural battery, sets the boundary conditions of the multifunctional structural battery, performs on-orbit thermal analysis, and obtains the temperature field distribution of the multifunctional structural battery; finally, it evaluates whether the temperature range and temperature difference of the multifunctional structural battery meet the index requirements. The present invention provides an effective active and passive integrated thermal control design scheme for multifunctional structural batteries of spacecraft, which meets the operating temperature requirements of the battery and the temperature difference requirements between single cells, and has good adaptability and reliability.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace thermal control technology, and in particular relates to an active and passive integrated thermal control design method for an aerospace multifunctional structural battery. Background Art

[0002] The power supply system is one of the main support systems of spacecraft, among which the power supply with the function of converting and storing electric energy is the key equipment that affects the performance, life and reliability of spacecraft. With the development of science and technology, a multifunctional structural battery integrating power supply, load bearing and vibration reduction has been developed in the field of spacecraft power supply, see patent document CN 105947235B "Multifunctional structure for electric energy and mechanical environment management". This new type of battery directly embeds the single cell into the cabin, which not only saves space, but also effectively absorbs the vibration of the cabin, and adapts to the requirements of space launch on the volume and mechanical environment of the spacecraft. However, the structural characteristics of this multifunctional structural battery bring difficulties to its thermal control design. Traditional spacecraft batteries are usually a single unit, and the thermal conductivity between each single cell is good, which is easy to meet the temperature difference requirements, and the physical interface between the battery and the spacecraft cabin or other equipment is clear and the coupling is small, so it is easy to adopt insulation and other measures to meet the working temperature requirements. The multifunctional structural battery is a distributed structure, the thermal conductivity between the single cells is poor, and it is highly coupled with the spacecraft structure. Its thermal control design is subject to many constraints and is difficult, which brings severe challenges to the design of its effective thermal control means. Summary of the invention

[0003] The main purpose of the present invention is to provide an active and passive integrated thermal control design method for aerospace multifunctional structural batteries, aiming to solve the technical problem that existing thermal control design methods are difficult to meet the operating temperature requirements of aerospace multifunctional structural batteries and the temperature difference requirements between each single battery.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is: an active and passive integrated thermal control design method for aerospace multifunctional structural batteries, comprising the following steps S1 to S5:

[0005] S1. Input the configuration, heat consumption parameters and thermophysical property parameters of the multifunctional structural battery;

[0006] The multifunctional structural battery comprises a battery support structure and a plurality of single cells;

[0007] S2. Designing distributed active control measures: selecting a thermal pad and a thermally conductive carbon fiber board with a thermal conductivity greater than a preset threshold, arranging multiple temperature measurement loops and multiple temperature control loops on the thermally conductive carbon fiber board, and setting a temperature control logic, wherein the temperature control logic controls the opening of each temperature control loop according to the measurement result of the temperature measurement loop;

[0008] S3. Design passive thermal control measures based on multi-level temperature control: Set passive thermal control measures for the multi-functional structure battery at three levels: component level, assembly level, and overall satellite level. The passive thermal control measures are to achieve passive temperature control by setting any one or more of thermal insulation materials, thermal insulation devices, and structural layouts.

[0009] S4. Establish a thermal analysis model of the multi-functional structure battery, set the boundary conditions of the multi-functional structure battery, and perform on-orbit operating condition thermal analysis based on the thermal analysis model according to the input parameters to obtain the temperature field distribution of the multi-functional structure battery.

[0010] S5. Evaluate whether the temperature range and / or temperature difference of the multi-functional structure battery obtained in step S4 meet the index requirements. If they meet, the design is completed; if not, adjust the layout forms of the temperature measurement circuit and the temperature control circuit, change the parameters of the temperature control logic, adjust the component-level passive thermal insulation measures and the overall satellite-level passive thermal insulation measures, and re-execute steps S2 - S5 to re-design the thermal control scheme of the multi-functional structure battery until the temperature range and temperature difference meet the index requirements.

[0011] Optionally, the preset threshold of the thermal conductivity of the thermally conductive carbon fiber board in step S2 is 5 W / mK; the thermal conductive pad is arranged on the surface of the single cell and is located between the single cell and the thermally conductive carbon fiber board.

[0012] Optionally, the thermally conductive carbon fiber board in step S2 uses M series carbon fiber; the thermal conductive pad uses a flexible thermal conductive material, and the thermal conductivity of the thermal conductive material is greater than 5 W / mK.

[0013] Optionally, the temperature measurement circuit in step S2 includes a thermistor for temperature measurement and a thermal control lower computer for control that are connected to each other; the temperature control circuit includes a heating sheet and a power supply that are connected to each other.

[0014] Optionally, the temperature control logic adopts a dual-interval temperature control method, including: Let T represent the temperature of the thermistor, ΔT represent the maximum allowable temperature difference, Tref represent the temperature of the central area of the multi-functional structure battery, Tmin represent the lower limit of the temperature control interval, and Tmax represent the upper limit of the temperature control interval. When the temperature T of the thermistor for temperature measurement is lower than the lower limit of the temperature control interval, that is, T < Tmin, or the temperature difference between the temperature T and the central area is greater than the maximum allowable temperature difference, that is, T < Tref - ΔT, the temperature control circuit is turned on; when the temperature T of the thermistor for temperature measurement is higher than the upper limit of the temperature control interval, that is, T > Tmax, or the temperature difference between the temperature T and the central area is greater than the maximum allowable temperature difference, that is, T > Tref + ΔT, the temperature control circuit is turned off.

[0015] Optionally, in step S3, the component-level passive insulation measure is: when the multifunctional structural battery is integrated into the integrated cabin panel, a thermal conductive material with a thermal conductivity lower than a preset threshold is filled between the multifunctional structural battery and the skin panel structure.

[0016] Optionally, in step S3, the component-level passive insulation measures are: coating the integrated cabin panel integrated with the multifunctional structural battery with multiple layers of insulation materials, and arranging any one or more of insulation gaskets, insulation pads and bolts with insulation function at the connection interface between the integrated cabin panel and other parts of the satellite body except the integrated cabin panel.

[0017] Optionally, in step S3, the passive insulation measures for the entire star are: optimizing the configuration of the spacecraft and the layout of the solar array, adjusting the position of the integrated cabin panel integrated with the multifunctional structural battery on the satellite body, so that the cabin panel is prevented from being directly radiated by the sun or radiated to the cold black space.

[0018] Optionally, in step S4, ANSYS software or UG software is used to establish a thermal analysis model of the multifunctional structural battery; the boundary condition of the multifunctional structural battery is specifically to set the side of the integrated cabin plate containing the multifunctional structural battery to a constant temperature.

[0019] Optionally, in step S5, the parameters of the temperature control logic include any one or more of an upper limit of a temperature control interval, a lower limit of a temperature control interval, and a maximum allowable temperature difference.

[0020] Compared with the existing conventional technologies, the beneficial technical effects achieved by the technical solution proposed in the present invention are mainly reflected in: the present invention provides an effective active and passive integrated thermal control design method for spacecraft multifunctional structural batteries, which meets the battery's operating temperature requirements and the temperature difference requirements between single cells, and has good adaptability and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0022] Figure 1 This is a schematic diagram of an integrated cabin panel containing multifunctional structural batteries being applied to a small satellite;

[0023] Figure 2 yes Figure 1 Exploded diagram of

[0024] Figure 3 It is a flow chart of the active and passive integrated thermal control design method of the aerospace multifunctional structural battery of the present invention;

[0025] Figure 4 It is a schematic diagram of the distributed active thermal control scheme of the multifunctional structural battery;

[0026] Figure 5 The thermal analysis model diagram of the multifunctional structural battery established using ANSYS software: (a) is the overall effect diagram; (b) is the effect diagram showing the internal battery;

[0027] Figure 6 It is the on-orbit temperature telemetry curve of the multifunctional structural battery;

[0028] Figure 7 It is a temperature difference curve diagram of the temperature measuring points of the multifunctional structure battery.

[0029] Reference numerals:

[0030] 1——integrated cabin panel; 2——satellite body; 3——solar cell array; 4——multifunctional structural battery; 5——skin panel structure; 6——battery support structure; 7——single battery; 8——thermal pad; 9——thermal conductive carbon fiber plate; 10——heating plate; 11——thermistor. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0032] The present invention relates to the research field of spacecraft thermal control, and specifically designs a thermal control design scheme combining active and passive aspects for a multifunctional structural battery on a spacecraft, so as to provide a suitable temperature environment for the multifunctional structural battery to meet the working temperature index requirements.

[0033] The multifunctional structural battery is an aerospace power supply equipment that integrates power supply, load bearing and vibration reduction functions. Figure 1 This is a specific embodiment of the multifunctional structural battery, which has a wide range of uses and is not limited to this embodiment. Figure 1 The application of an integrated cabin panel containing multifunctional structural batteries to a small satellite is demonstrated. The satellite body 2 of the small satellite is a cube structure, consisting of six cabin panels: front, rear, left, right, top and bottom. An integrated cabin panel containing multifunctional structural batteries is adopted on the right cabin panel with a solar cell array 3 on one side. Figure 2 Given Figure 1The multifunctional structural battery 4 is a flat square structure, which is composed of a battery support structure 6 and a plurality of single batteries 7 (see Figure 4 ), a skin panel structure 5 is arranged on both sides of the multifunctional structural battery 4, thus forming an integrated cabin panel 1 containing a multifunctional structural battery, which can be directly used as a cabin panel structure of a small satellite.

[0034] The present invention is directed to Figure 1 The small satellite embodiment shown in the figure provides an active and passive integrated thermal control design method for aerospace multifunctional structural batteries. The flow chart of the active and passive integrated thermal control design method is as follows: Figure 3 shown.

[0035] The comprehensive thermal control design method includes two types of thermal control measures: distributed active thermal control measures and passive thermal control measures based on multi-stage temperature control. The distributed active thermal control measures include thermal conductive carbon fiber plates, thermal conductive pads, distributed temperature measurement and control loops, etc.; the passive thermal control measures based on multi-stage temperature control include silicone rubber, aluminum honeycomb, multi-layer thermal insulation materials, thermal insulation pads, solar cell array shielding, etc.

[0036] See Figure 3 The active and passive integrated thermal control design method comprises the following steps S1 to S5:

[0037] S1. Input the configuration, heat consumption parameters and thermophysical property parameters of the multifunctional structural battery;

[0038] In this embodiment, the configuration of the multifunctional structural battery is a multi-chip lithium-ion battery configuration, and multiple lithium-ion batteries are arranged in a row to form a battery pack to provide power for the spacecraft. The heat consumption parameters of the multifunctional structural battery mainly include the heat generated during charging and the heat generated during discharging, and the thermal physical property parameters mainly include structural mass, thermal conductivity, specific heat capacity, etc. The present invention proposes a thermal control design method combining active and passive control for the multifunctional structural battery, and designs distributed active control measures and passive thermal control measures based on multi-stage temperature control respectively.

[0039] S2. Designing distributed active control measures: selecting a thermal pad and a thermally conductive carbon fiber board with a thermal conductivity greater than a preset threshold, arranging multiple temperature measurement loops and multiple temperature control loops on the thermally conductive carbon fiber board, and setting a temperature control logic, wherein the temperature control logic controls the opening of each temperature control loop according to the measurement result of the temperature measurement loop;

[0040] The distributed active thermal control measures mainly include a thermal conductive carbon fiber plate 9, a thermal conductive pad 8, a distributed temperature measurement circuit and a temperature control circuit, etc. Figure 4 .

[0041] The thermal conductivity parameter of the described thermal conductive carbon fiber plate 9 is greater than a certain preset threshold value, which is mainly used to balance the temperatures of each single battery 7. M series carbon fibers can be selected, which have the characteristics of high thermal conductivity coefficient and high elastic modulus. Taking M55J carbon fiber as an example, its thermal conductivity coefficient is 20 W / mK and its elastic modulus is 540 GPa. In this embodiment, the preset threshold value is selected as 5 W / mK, that is, it is required that the thermal conductivity coefficient of the thermal conductive carbon fiber plate 9 is greater than 5 W / mK.

[0042] The described thermal conductive pad 8 is made of a high thermal conductivity material with a thermal conductivity coefficient greater than 5 W / mK, and at the same time has a certain flexibility to achieve close contact with the thermal conductive carbon fiber plate 9 and the single battery 7, so as to achieve the purpose of high-efficiency heat transfer. The thermal conductive pad 8 is arranged on the surface of the single battery 7 and is located between the single battery 7 and the thermal conductive carbon fiber plate 9.

[0043] The described distributed temperature measurement circuit and temperature control circuit divide the area where the single battery 7 is located into several areas, and a thermistor 11 and multiple heating sheets 10 are respectively arranged in each area, so as to form multiple temperature measurement circuits and temperature control circuits.

[0044] The temperature measurement circuit includes a thermistor for temperature measurement and a lower computer for thermal control that are connected to each other; the temperature control circuit includes a heating sheet and a power supply that are connected to each other.

[0045] Each temperature control circuit uses the signal of the corresponding thermistor 11 as a reference, and the temperature control logic adopts a two-interval temperature control strategy to control the working state of the temperature control circuit through the logic of two-interval temperature control.

[0046] The described temperature control logic adopts a two-interval temperature control method, and the logic of this two-interval temperature control method is as follows:

[0047] Let T represent the temperature of the thermistor, ΔT represent the maximum allowable temperature difference, Tref represent the temperature of the central area of the multi-functional structure battery, Tmin represent the lower limit of the temperature control interval, and Tmax represent the upper limit of the temperature control interval. When the temperature T of the thermistor for temperature measurement is lower than the lower limit of the temperature control interval, that is, T < Tmin, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, that is, T < Tref - ΔT, the temperature control circuit is turned on; when the temperature T of the thermistor for temperature measurement is higher than the upper limit of the temperature control interval, that is, T > Tmax, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, that is, T > Tref + ΔT, the temperature control circuit is turned off.

[0048] S3. Design passive thermal control measures based on multi-level temperature control: Set passive thermal control measures for the multi-functional structure battery from three levels: component level, assembly level, and overall satellite level. The passive thermal control measures are to achieve passive temperature control by setting any one or more of thermal insulation materials, thermal insulation devices, and structural layouts;

[0049] The passive thermal control measures based on multi-stage temperature control are designed for multifunctional structural batteries from component level, assembly level and whole star level.

[0050] The passive insulation measures at the component level are: when the multifunctional structural battery is integrated into the integrated cabin panel, a thermal conductive material with a thermal conductivity lower than a preset threshold is filled between the multifunctional structural battery and the skin panel structure, such as gaskets, aluminum honeycombs and other materials with thermal insulation properties.

[0051] Passive insulation measures at the component level are: coating the integrated cabin panel integrated by the multifunctional structural battery with multiple layers of insulation materials, and arranging any one or more of insulation gaskets, insulation pads, and insulation bolts at the connection interface between the integrated cabin panel and other parts of the satellite body except the integrated cabin panel. Specifically, the integrated cabin panel 1 integrated by the multifunctional structural battery is thermally insulated from other cabin panels or equipment of the satellite body 2. The surface of the integrated cabin panel 1 is coated with multiple layers of insulation materials to reduce the radiation heat exchange between the integrated cabin panel 1 and other equipment on the satellite body. At the installation interface between the integrated cabin panel 1 and other cabin panels and equipment of the satellite body 2, insulation gaskets or insulation pads are added, or insulation bolts are installed.

[0052] The passive heat insulation measures for the whole star are: optimizing the configuration of the spacecraft and the layout of the solar array, adjusting the position of the integrated cabin panel integrated by the multifunctional structural battery on the satellite body, so that the cabin panel avoids direct solar radiation or radiation to the cold black space. In this embodiment, when designing the configuration of the spacecraft and the layout of the solar array 3, the integrated cabin panel 1 integrated by the multifunctional structural battery is located between the satellite body 2 and the solar array 3, and its plane avoids direct solar radiation and cold black background space radiation, and avoids the cabin panel being in a lower or higher environment.

[0053] S4. Establish a thermal analysis model of the multifunctional structural battery, set boundary conditions of the multifunctional structural battery, perform on-orbit thermal analysis according to input parameters based on the thermal analysis model, and obtain a temperature field distribution of the multifunctional structural battery;

[0054] ANSYS software is a large-scale general-purpose finite element analysis (FEA) software developed by ANSYS of the United States. It is the fastest growing computer-aided engineering (CAE) software in the world. It can interface with most computer-aided design (CAD, computer Aided design) software to achieve data sharing and exchange, such as Creo, NASTRAN, Algor, I-DEAS, AutoCAD, etc. It is a large-scale general-purpose finite element analysis software that integrates structure, fluid, electric field, magnetic field, and acoustic field analysis. It has a wide range of applications in the fields of nuclear industry, railways, petrochemicals, aerospace, machinery manufacturing, energy, automobile transportation, national defense and military industry, electronics, civil engineering, shipbuilding, biomedicine, light industry, mining, water conservancy, and daily household appliances.

[0055] ANSYS is powerful. In addition to conventional static and dynamic analysis of structures, it can also perform thermal analysis of structures. In this embodiment, ANSYS software is used to establish a thermal analysis model of a functional structural battery. Figure 5 shown.

[0056] In addition, UG software can also be used to establish a thermal analysis model for functional structural batteries. UG (UnigraphicsNX) is a product engineering solution produced by Siemens PLM Software. It is a three-dimensional parametric software that integrates CAD / CAM / CAE (computer-aided design, computer-aided manufacturing and computer-aided engineering). It is one of the most advanced and popular industrial design software today. It combines the functions of conceptual design, engineering design, analysis and processing and manufacturing. It can provide digital modeling and verification methods for users' product design and processing processes, and can easily realize the construction of various complex entities and shapes. It is widely used in machinery, automobiles, home appliances, chemicals, aerospace and other fields. UG software can also be used for thermal analysis of structures.

[0057] After establishing the thermal analysis model of the functional structural battery, the boundary conditions of the multifunctional structural battery are further set. Specifically, the four sides of the integrated cabin panel 1 containing the multifunctional structural battery are set to a constant temperature (the constant temperature is obtained by the thermal analysis of the spacecraft), and then the thermal analysis of the on-orbit working conditions is carried out to obtain the temperature field distribution of the multifunctional structural battery.

[0058] S5. Evaluate whether the temperature range and / or temperature difference of the multifunctional structural battery obtained in step S4 meets the index requirements. If so, the design is completed; if not, adjust the layout of the temperature measurement loop and the temperature control loop, change the parameters of the temperature control logic, adjust the component-level passive insulation measures and the whole-star passive insulation measures, and re-execute steps S2 to S5 to redesign the thermal control scheme of the multifunctional structural battery until the temperature range and temperature difference meet the index requirements.

[0059] The parameters of the temperature control logic include any one or more of an upper limit of the temperature control interval, a lower limit of the temperature control interval and a maximum allowable temperature difference.

[0060] Finally, the effect of the heat dissipation system is described by an application example of the present invention. Assume that the temperature control range is required to be 10°C to 35°C, that is, the upper limit of the temperature control range is 35°C and the lower limit is 10°C; the maximum allowable temperature difference ΔT is 5°C.

[0061] The thermal conductive carbon fiber plate 9 adopts an M40 carbon fiber plate with a thickness of 2 mm, and the thermal conductive pad 8 adopts a thermal conductive plate with a thickness of 1 mm and a model of SP2000 / 025-DT. The multifunctional structural battery 4 is installed on the aluminum honeycomb cabin plate through a K216 silicone rubber gasket with a thickness of 2 mm. At the connection interface between the integrated cabin plate containing the multifunctional structural battery and the other parts of the satellite body, a K216 silicone rubber gasket with a thickness of 2 mm is arranged for heat insulation. A plurality of heating plates 10 are pasted on the outer surface of the thermal conductive carbon fiber plate 9, and the position of each heating plate 10 corresponds to the position of each single battery 7. First, the area where the single battery 7 is located is divided into 4 areas, and a heating plate 10 is pasted on the upper cover plate position corresponding to each single battery 7. Four main heating circuits and four backup heating circuits are formed by series-parallel connection. Thermistors 11 for temperature control are respectively installed at the corner points A, B, C, and D of the four zones, see. Figure 4 . 10 units of multi-layer heat insulation materials are installed on the inner side of the integrated cabin panel 1, and 15 units of multi-layer heat insulation materials are installed on the outer side. The inner side of the integrated cabin panel 1 is connected to other cabin panels through a 3mm thick polyimide heat insulation pad. The solar cell array 3 is installed on the outer side of the cabin panel through titanium alloy screws and polyimide heat insulation pads.

[0062] Figure 6 This is the on-orbit temperature telemetry curve of the multifunctional structural battery. Figure 7 is the temperature difference of the temperature measuring point of the structural battery. Figure 6 and Figure 7 It can be seen that the temperature range of the multifunctional structure battery is 15.8℃~20.9℃, which meets the operating temperature requirement of 10℃~35℃. The maximum temperature difference of the temperature measurement point is 4.50℃, which meets the requirement of no more than 5℃.

[0063] Although the content of the present invention is described in detail through the above embodiments, it is not intended to limit the present invention. Any person skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the scope defined in the claims.

Claims

1. A method for designing active and passive integrated thermal control of aerospace multifunctional structural batteries, characterized in that: It includes the following steps S1 to S5: S1. Input the configuration, heat dissipation parameters, and thermal physical properties parameters of the multi-functional structure battery; The multi-functional structure battery includes a battery support structure and multiple single cells; S2. Design distributed active control measures: Select a thermal conductive pad and a thermal conductive carbon fiber plate with a thermal conductivity greater than a preset threshold. Arrange multiple temperature measurement circuits and multiple temperature control circuits on the thermal conductive carbon fiber plate, and set a temperature control logic, where the temperature control logic is to control the opening of each temperature control circuit according to the measurement results of the temperature measurement circuits; S3. Design passive thermal control measures based on multi-level temperature control: Set passive thermal control measures for the multi-functional structure battery from three levels: component level, assembly level, and overall satellite level. The passive thermal control measures are to achieve passive temperature control by setting any one or more of thermal insulation materials, thermal insulation devices, and structural layouts; S4. Establish a thermal analysis model of the multi-functional structure battery, set the boundary conditions of the multi-functional structure battery, and perform on-orbit condition thermal analysis based on the thermal analysis model according to the input parameters to obtain the temperature field distribution of the multi-functional structure battery; S5. Evaluate whether the temperature range and / or temperature difference of the multi-functional structure battery obtained in step S4 meet the index requirements. If they meet, the design is completed; if not, adjust the layout form of the temperature measurement circuit and the temperature control circuit, change the parameters of the temperature control logic, adjust the passive thermal insulation measures at the assembly level and the overall satellite level, and re-execute steps S2 to S5 to re-design the thermal control scheme of the multi-functional structure battery until the temperature range and temperature difference meet the index requirements; In step S2, the temperature measurement circuit includes a thermistor for temperature measurement and a thermal control lower computer for control, which are connected to each other; the temperature control circuit includes a heating sheet and a power supply, which are connected to each other; The temperature control logic adopts a two-interval temperature control method, including: Let T represent the temperature of the thermistor, ΔT represent the maximum allowable temperature difference, Tref represent the temperature of the central area of the multi-functional structure battery, Tmin represent the lower limit of the temperature control interval, and Tmax represent the upper limit of the temperature control interval. When the temperature T of the thermistor for temperature measurement is lower than the lower limit of the temperature control interval, that is, T < Tmin, or the temperature difference between the temperature T and the central area is greater than the maximum allowable temperature difference, that is, T < Tref - ΔT, the temperature control circuit is turned on; when the temperature T of the thermistor for temperature measurement is higher than the upper limit of the temperature control interval, that is, T > Tmax, or the temperature difference between the temperature T and the central area is greater than the maximum allowable temperature difference, that is, T > Tref + ΔT, the temperature control circuit is turned off.

2. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to claim 1 is characterized in that: In step S2, the preset threshold of the thermal conductivity of the thermal conductive carbon fiber plate is 5 W / mK; the thermal conductive pad is arranged on the surface of the single cell and is located between the single cell and the thermal conductive carbon fiber plate.

3. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to claim 1 is characterized in that: In step S2, the thermal conductive carbon fiber plate adopts M series carbon fiber; the thermal conductive pad adopts a flexible thermal conductive material, and the thermal conductivity of the thermal conductive material is greater than 5 W / mK.

4. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to any one of claims 1 to 3, characterized in that: In step S3, the component-level passive insulation measure is: when the multifunctional structural battery is integrated into the integrated cabin panel, a thermal conductive material with a thermal conductivity lower than a preset threshold is filled between the multifunctional structural battery and the skin panel structure.

5. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to any one of claims 1 to 3, characterized in that: In step S3, the passive insulation measures at the component level are: the integrated cabin panel integrated with the multifunctional structural battery is coated with multiple layers of insulation materials, and any one or more of insulation gaskets, insulation pads and bolts with insulation function are arranged at the connection interface between the integrated cabin panel and other parts of the satellite body except the integrated cabin panel.

6. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to any one of claims 1 to 3, characterized in that: In step S3, the passive insulation measures for the entire star are: optimizing the configuration of the spacecraft and the layout of the solar array, adjusting the position of the integrated cabin panel integrated with the multifunctional structural battery on the satellite body, so that the cabin panel is prevented from being directly radiated by the sun or radiated to the cold black space.

7. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to any one of claims 1 to 3, characterized in that: In step S4, ANSYS software or UG software is used to establish a thermal analysis model of the multifunctional structural battery; the boundary condition of the multifunctional structural battery is specifically to set the side of the integrated cabin plate containing the multifunctional structural battery to a constant temperature.

8. The active and passive integrated thermal control design method for aerospace multifunctional structural batteries according to any one of claims 1 to 3, characterized in that: In step S5, the parameters of the temperature control logic include any one or more of an upper limit of the temperature control interval, a lower limit of the temperature control interval and a maximum allowable temperature difference.

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