CN114154243A - Active and passive comprehensive thermal control design method for aerospace multifunctional structure battery - Google Patents
Active and passive comprehensive thermal control design method for aerospace multifunctional structure battery Download PDFInfo
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Abstract
The invention discloses an active and passive comprehensive thermal control design method for a battery with a multifunctional aerospace structure, and belongs to the technical field of aerospace thermal control. Firstly, respectively designing a distributed active control measure and a passive thermal control measure based on multi-stage temperature control according to the configuration, the heat consumption parameter and the thermophysical property parameter of the multifunctional structural battery; then, establishing a thermal analysis model of the multifunctional structural battery by adopting commercial thermal analysis software, setting boundary conditions of the multifunctional structural battery, and carrying out on-orbit working condition thermal analysis to obtain the temperature field distribution of the multifunctional structural battery; and finally, evaluating whether the temperature range and the temperature difference of the multifunctional structural battery meet the index requirements. The invention provides an effective active and passive comprehensive thermal control design scheme for the spacecraft multifunctional structure battery, meets the working temperature requirement of the battery and the temperature difference requirement between single batteries, and has good adaptability and reliability.
Description
Technical Field
The invention belongs to the technical field of aerospace thermal control, and particularly relates to an active and passive comprehensive thermal control design method for an aerospace multifunctional structural battery.
Background
The power supply system is one of the main guarantee systems of the spacecraft, wherein the power supply with the functions of converting and storing electric energy is the key equipment influencing the performance, service life and reliability of the spacecraft. With the development of science and technology, a multifunctional battery integrating power supply, bearing and vibration reduction functions is developed in the field of spacecraft power supplies at present, see patent document CN 105947235B "multifunctional structure for managing electric energy and mechanical environment". The novel battery directly embeds the single battery into the cabin plate, thereby not only saving space, but also effectively absorbing the vibration of the cabin plate, and meeting the requirements of space launch on the size and the mechanical environment of the spacecraft. However, the structural features of such a multifunctional structural battery present difficulties in its thermal control design. The traditional spacecraft battery is usually a single battery, the thermal conductivity among all single batteries is good, the temperature difference requirement is easily met, the physical interfaces of the battery and a spacecraft cabin plate or other equipment are clear, the coupling is small, and measures such as heat insulation are easily adopted to meet the working temperature requirement. The multifunctional structure battery is a distributed structure, the heat conductivity among the single batteries is poor, the single batteries are highly coupled with the structure of the spacecraft, the thermal control design is more restricted and difficult, and thus, the effective thermal control means design is provided with serious challenges.
Disclosure of Invention
The invention mainly aims to provide an active and passive comprehensive thermal control design method for an aerospace multifunctional structure battery, and aims to solve the technical problems that the existing thermal control design method is difficult to meet the working temperature requirement of the aerospace multifunctional structure battery and the temperature difference requirement among single batteries.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows: an active and passive comprehensive thermal control design method of a space multifunctional structure battery comprises the following steps of S1-S5:
s1, inputting the configuration, heat consumption parameters and thermophysical parameters of the multifunctional structural battery;
the multifunctional structure battery comprises a battery supporting structure and a plurality of single batteries;
s2, carrying out distributed active control measure design: selecting a heat conduction pad and a heat conduction carbon fiber plate with a heat conductivity coefficient larger than a preset threshold value, arranging a plurality of temperature measurement loops and a plurality of temperature control loops on the heat conduction carbon fiber plate, 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 loops;
s3, carrying out passive thermal control measure design based on multi-stage temperature control: setting passive thermal control measures for the multifunctional structural battery from three levels of a component level, an assembly level and a whole star level, wherein the passive thermal control measures are used for realizing passive temperature control by setting any one or more of heat insulation materials, heat insulation devices and structural layouts;
s4, establishing a thermal analysis model of the multifunctional structural battery, setting boundary conditions of the multifunctional structural battery, and performing on-orbit working condition thermal analysis according to input parameters based on the thermal analysis model to obtain the temperature field distribution of the multifunctional structural battery;
s5, evaluating whether the temperature range and/or the temperature difference of the multifunctional structural battery obtained in the step S4 meet the index requirements, and if so, ending the design; if the temperature difference does not meet the index requirements, the arrangement forms of the temperature measuring loop and the temperature control loop are adjusted, the parameters of the temperature control logic are changed, the component-level passive heat insulation measures and the whole-star-level passive heat insulation measures are adjusted, and the steps S2 to S5 are executed again to redesign the thermal control scheme of the multifunctional structural battery until the temperature range and the temperature difference meet the index requirements.
Optionally, in step S2, the preset threshold of the thermal conductivity of the thermal conductive carbon fiber plate is 5W/mK; the heat conducting pad is arranged on the surface of the single battery and is positioned between the single battery and the heat conducting carbon fiber plate.
Optionally, in step S2, the heat-conducting carbon fiber plate is an M-series carbon fiber; the heat conduction pad is made of flexible heat conduction materials, and the heat conduction coefficient of the heat conduction materials is larger than 5W/mK.
Optionally, in step S2, the temperature measurement loop includes a thermistor for measuring temperature and a thermal control lower computer for controlling, which are connected to each other; the temperature control loop comprises a heating sheet and a power supply which are connected with each other.
Optionally, the temperature control logic adopts a dual-zone temperature control mode, including: setting T to represent the temperature of the thermistor, delta T to represent the maximum allowable temperature difference, Tref to represent the temperature of the central area of the multifunctional structure battery, Tmin to represent the lower limit of a temperature control interval, Tmax to represent the upper limit of the temperature control interval, and when the temperature T of the thermistor for temperature measurement is lower than the lower limit of the temperature control interval, namely T < Tmin, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, namely T < Tref-delta T, starting the temperature control loop; and when the temperature T of the thermistor for measuring the temperature is higher than the upper limit of the temperature control interval, namely T is greater than Tmax, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, namely T is greater than Tref + delta T, closing the temperature control loop.
Optionally, in step S3, the component-level passive heat insulation measure is: when the multifunctional structure battery is integrated into the integrated cabin plate, a heat conduction material with the heat conductivity lower than a preset threshold value is filled between the multifunctional structure battery and the skin panel structure.
Optionally, in step S3, the module-level passive thermal insulation measure is: the integrated cabin plate integrated by the multifunctional structure battery is coated with a plurality of layers of heat insulation materials, and any one or more than two of a heat insulation gasket, a heat insulation pad and a bolt with a heat insulation function are arranged at the connecting interface between the integrated cabin plate and other parts of the satellite body except the integrated cabin plate.
Optionally, in step S3, the whole-star-level passive heat insulation measure is: the configuration of the spacecraft and the layout of the solar cell array are optimized, and the position of the integrated cabin plate integrated by the multifunctional structural cell on the satellite body is adjusted, so that the cabin plate is prevented from directly receiving solar radiation or radiating to a cold and black space.
Optionally, in step S4, establishing a thermal analysis model of the multifunctional structured battery by using ANSYS software or UG software; the boundary condition of the multifunctional structural battery is specifically that the side surface of the integrated cabin plate containing the multifunctional structural battery is set to be at a constant temperature.
Optionally, in step S5, the parameter of the temperature control logic includes 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.
Compared with the prior conventional technology, the technical scheme provided by the invention has the following beneficial technical effects: the invention provides an effective active and passive comprehensive thermal control design method for a spacecraft multifunctional structure battery, meets the working temperature requirement of the battery and the temperature difference requirement between single batteries, and has good adaptability and reliability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic view of an integrated deck containing a battery of multifunctional construction for use with a small satellite;
FIG. 2 is an exploded view of FIG. 1;
FIG. 3 is a flow chart of an active and passive integrated thermal control design method of the aerospace multifunctional structure battery according to the invention;
FIG. 4 is a schematic diagram of a distributed active thermal control scheme for a multi-functional structural battery;
fig. 5 is a diagram of a thermal analysis model of a multifunctional structured battery built using ANSYS software: (a) is an overall effect graph; (b) is an effect diagram for displaying the internal battery;
FIG. 6 is an in-orbit temperature telemetry plot for a multi-functional structural battery;
FIG. 7 is a temperature difference graph of the temperature measuring point of the multifunctional structured battery.
Reference numerals:
1-integral deck board; 2-satellite body; 3-solar cell array; 4-multifunctional structural battery; 5-skin panel structure; 6-battery support structure; 7-single cell; 8-heat conducting pad; 9-heat conductive carbon fiber plate; 10-heating plate; 11-thermistor.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention relates to the field of spacecraft thermal control research, in particular to an active-passive combined thermal control design scheme designed for a multifunctional structural battery on a spacecraft, which provides a proper temperature environment for the multifunctional structural battery so as to meet the requirement of a working temperature index.
The multifunctional structure battery is an aerospace power supply device integrating power supply, bearing and vibration reduction functions, and fig. 1 is a specific embodiment of the multifunctional structure battery, which is very wide in application range and is not limited to the specific embodiment. Fig. 1 shows a situation that the integrated deck plate containing the multifunctional battery is applied to a certain small satellite, a satellite body 2 of the small satellite is of a cubic structure and consists of six deck plates, namely a front deck plate, a rear deck plate, a left deck plate, a right deck plate, an upper deck plate and a lower deck plate, and the integrated deck plate containing the multifunctional battery is arranged on the right deck plate, on one side of which a solar sailboard 3 is arranged. Fig. 2 shows an exploded view of the structure of fig. 1. The multifunctional structure battery 4 is a flat square structure and is composed of a battery supporting structure 6 and a plurality of single batteries 7 (see fig. 4), and skin panel structures 5 are arranged on two sides of the multifunctional structure battery 4, so that an integrated cabin plate 1 containing the multifunctional structure battery is formed and can be directly used as a cabin plate structure of a small satellite.
The invention provides an active and passive integrated thermal control design method of a multifunctional aerospace structure battery aiming at the minisatellite embodiment shown in figure 1, and a flow chart of the active and passive integrated thermal control design method is shown in figure 3.
The comprehensive thermal control design method comprises 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 comprise a heat conduction carbon fiber plate, a heat conduction pad, a distributed temperature measurement and control loop and the like; the passive thermal control measures based on the multi-stage temperature control comprise silicon rubber, aluminum honeycomb, multi-layer thermal insulation materials, thermal insulation pads, solar cell array shielding and the like.
In detail, referring to fig. 3, the active and passive integrated thermal control design method includes the following steps S1 to S5:
s1, inputting the configuration, heat consumption parameters and thermophysical parameters of the multifunctional structural battery;
in this embodiment, the configuration of the multifunctional battery is a multi-piece lithium ion battery configuration, and the multi-piece lithium ion batteries are arranged in an array to form a battery pack to provide electric energy for the spacecraft. The heat consumption parameters of the multifunctional structure battery mainly comprise heat productivity in a charging process and heat productivity in a discharging process, and the thermophysical parameters mainly comprise structure quality, heat conductivity coefficient, specific heat capacity and the like. Aiming at the multifunctional structure battery, the invention provides an active and passive combined thermal control design method, which respectively designs distributed active control measures and passive thermal control measures based on multi-stage temperature control.
S2, carrying out distributed active control measure design: selecting a heat conduction pad and a heat conduction carbon fiber plate with a heat conductivity coefficient larger than a preset threshold value, arranging a plurality of temperature measurement loops and a plurality of temperature control loops on the heat conduction carbon fiber plate, 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 loops;
the distributed active thermal control measure mainly comprises a heat-conducting carbon fiber plate 9, a heat-conducting pad 8, a distributed temperature measurement loop, a temperature control loop and the like, and is shown in fig. 4.
The heat conduction parameter of the heat conduction carbon fiber plate 9 is larger than a certain preset threshold value, the heat conduction parameter is mainly used for balancing the temperature of each single battery 7, M series carbon fibers can be selected, the heat conduction parameter is high, the elastic modulus is high, and the heat conduction parameter is 20W/mK and the elastic modulus is 540GPa when M55J carbon fibers are taken as an example. In this embodiment, the preset threshold is selected to be 5W/mK, that is, the thermal conductivity of the thermal conductive carbon fiber plate 9 is required to be greater than 5W/mK.
The heat conducting pad 8 is made of high heat conducting materials with the heat conducting coefficient larger than 5W/mK, has certain flexibility, and is in close contact with the heat conducting carbon fiber plate 9 and the single battery 7, so that the purpose of high-efficiency heat transfer is achieved. The heat conducting pad 8 is disposed on the surface of the single battery 7 and located between the single battery 7 and the heat conducting carbon fiber plate 9.
The distributed temperature measurement loop and the temperature control loop divide the area where the single battery 7 is located into a plurality of areas, and each area is respectively provided with the thermistor 11 and the heating sheets 10, so that a plurality of temperature measurement loops and a plurality of temperature control loops are formed.
The temperature measuring loop comprises a thermistor and a thermal control lower computer, wherein the thermistor is used for measuring temperature and the thermal control lower computer is used for controlling; the temperature control loop comprises a heating sheet and a power supply which are connected with each other.
Each temperature control loop adopts the signal of the corresponding thermistor 11 as reference, the temperature control logic adopts a dual-zone temperature control strategy, and the working state of the temperature control loop is controlled through the dual-zone temperature control logic.
The temperature control logic adopts a double-zone temperature control mode, and the logic of the double-zone temperature control mode is as follows:
setting T to represent the temperature of the thermistor, delta T to represent the maximum allowable temperature difference, Tref to represent the temperature of the central area of the multifunctional structure battery, Tmin to represent the lower limit of a temperature control interval, Tmax to represent the upper limit of the temperature control interval, and when the temperature T of the thermistor for temperature measurement is lower than the lower limit of the temperature control interval, namely T < Tmin, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, namely T < Tref-delta T, starting the temperature control loop; and when the temperature T of the thermistor for measuring the temperature is higher than the upper limit of the temperature control interval, namely T is greater than Tmax, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, namely T is greater than Tref + delta T, closing the temperature control loop.
S3, carrying out passive thermal control measure design based on multi-stage temperature control: setting passive thermal control measures for the multifunctional structural battery from three levels of a component level, an assembly level and a whole star level, wherein the passive thermal control measures are used for realizing passive temperature control by setting any one or more of heat insulation materials, heat insulation devices and structural layouts;
the passive thermal control measures based on the multi-stage temperature control are designed for multifunctional structural batteries from a component level, an assembly level and an integral star level respectively.
The component-level passive heat insulation measures are as follows: when the multifunctional structural battery is integrated into the integrated cabin plate, a heat conduction material with the heat conductivity lower than a preset threshold value, such as a gasket, an aluminum honeycomb and other materials with a heat insulation effect, is filled between the multifunctional structural battery and the skin panel structure.
The assembly-level passive heat insulation measures are as follows: the integrated cabin plate integrated by the multifunctional structure battery is coated with a plurality of layers of heat insulation materials, and any one or more than two of a heat insulation gasket, a heat insulation pad and a bolt with a heat insulation function are arranged at the connecting interface between the integrated cabin plate and other parts of the satellite body except the integrated cabin plate. In particular, the integrated deck 1, integrated by the multifunctional structural battery, is thermally insulated from other decks or equipment of the satellite body 2. The surface of the integrated cabin plate 1 is coated with multiple layers of heat insulation materials, so that the radiation heat exchange between the integrated cabin plate 1 and other star-shaped equipment is reduced. And a heat insulation gasket or a heat insulation pad is additionally arranged at the installation interface of the integrated cabin plate 1 and other cabin plates and equipment of the satellite body 2, or a bolt with a heat insulation function is installed.
The whole-star-level passive heat insulation measures are as follows: the configuration of the spacecraft and the layout of the solar cell array are optimized, and the position of the integrated cabin plate integrated by the multifunctional structural cell on the satellite body is adjusted, so that the cabin plate is prevented from directly receiving solar radiation or radiating to a cold and black space. In this embodiment, when designing the configuration of the spacecraft and the layout of the solar cell array 3, the integrated deck 1 integrated with the multifunctional structural battery is located between the satellite body 2 and the solar cell array 3, and the plane thereof avoids directly receiving solar radiation and cold-black background space radiation, and avoids the deck being in a lower or higher environment.
S4, establishing a thermal analysis model of the multifunctional structural battery, setting boundary conditions of the multifunctional structural battery, and performing on-orbit working condition thermal analysis according to input parameters based on the thermal analysis model to obtain the temperature field distribution of the multifunctional structural battery;
ANSYS software is large-scale general Finite Element Analysis (FEA) software developed by American ANSYS company, is Computer Aided Engineering (CAE) software growing fastest worldwide, can be interfaced with most Computer Aided Design (CAD) software to realize sharing and exchanging of data, such as Creo, NASTRAN, Algor, I-DEAS, AutoCAD and the like. The method is large-scale universal finite element analysis software integrating structure analysis, fluid analysis, electric field analysis, magnetic field analysis and sound field analysis. The composite material has wide application in the fields of nuclear industry, railways, petrochemical industry, aerospace, machine manufacturing, energy, automobile traffic, national defense and military industry, electronics, civil engineering, shipbuilding, biomedicine, light industry, ground and mining, water conservancy, household appliances for daily use and the like.
The ANSYS has powerful functions, and can be used for performing thermal analysis on the structure in addition to static and dynamic analysis on the conventional structure. In this embodiment, ANSYS software is used to create a thermal analysis model of the functional structure battery, as shown in fig. 5.
In addition, UG software can be adopted to establish a thermal analysis model of the functional structure battery. UG (Unigraphics NX) is a product engineering solution produced by Siemens PLM Software company, is three-dimensional parameterized Software integrating CAD/CAM/CAE (computer aided design, computer aided manufacturing and computer aided engineering), is one of the most advanced and popular industrial design Software at present, integrates functions of conceptual design, engineering design, analysis and processing manufacture, can provide digital modeling and verification means for product design and processing process of users, can easily realize the construction of various complex entities and models, and is widely applied to the fields of machinery, automobiles, household appliances, chemical engineering, aerospace and the like. UG software can also be used for thermal analysis of the structure.
After establishing the thermal analysis model of the functional structure battery, further setting the boundary conditions of the multifunctional structure battery, specifically: 4 side surfaces of the integrated cabin plate 1 containing the multifunctional structure battery are set to be constant temperature (the constant temperature is obtained by spacecraft thermal analysis), and then thermal analysis of on-orbit working conditions is carried out to obtain the temperature field distribution of the multifunctional structure battery.
S5, evaluating whether the temperature range and/or the temperature difference of the multifunctional structural battery obtained in the step S4 meet the index requirements, and if so, ending the design; if the temperature difference does not meet the index requirements, the arrangement forms of the temperature measuring loop and the temperature control loop are adjusted, the parameters of the temperature control logic are changed, the component-level passive heat insulation measures and the whole-star-level passive heat insulation measures are adjusted, and the steps S2 to S5 are executed again to redesign the thermal control scheme of the multifunctional structural battery until the temperature range and the temperature difference meet the index requirements.
The parameters of the temperature control logic comprise any one or more than two of the upper limit of the temperature control interval, the lower limit of the temperature control interval and the maximum allowable temperature difference.
Finally, the effect of the heat dissipation system is explained through an application example of the invention. Assuming that the temperature control interval is required to be 10-35 ℃, namely the upper limit of the temperature control interval is 35 ℃ and the lower limit is 10 ℃; the maximum allowable temperature difference Δ T is 5 ℃.
The heat-conducting carbon fiber plate 9 is an M40 carbon fiber plate with the thickness of 2mm, and the heat-conducting pad 8 is a heat-conducting plate with the thickness of 1mm and the model of SP 2000/025-DT. The multifunctional structural battery 4 is mounted on the aluminum honeycomb deck through a K216 silicone rubber gasket having a thickness of 2 mm. At the connecting interface between the integrated deck containing the multifunctional structural battery and the rest of the satellite body, a K216 silicone rubber gasket with the thickness of 2mm is arranged for heat insulation. A plurality of heating sheets 10 are adhered to the outer surface of the heat-conducting carbon fiber plate 9, and the position of each heating sheet 10 corresponds to the position of each single battery 7. Firstly, the area where the single battery 7 is located is divided into 4 areas, a heating sheet 10 is pasted on the position of an upper cover plate corresponding to each single battery 7, 4 main heating loops and 4 backup heating loops are formed in a series-parallel connection mode, and thermistors 11 for controlling temperature are respectively installed on corner points A, B, C, D of the 4 areas, which is shown in fig. 4. The integrated deck 1 is provided with 10 units of multi-layer insulation materials on the inner side and 15 units of multi-layer insulation materials on the outer side. The inner side of the integrated deck plate 1 is connected with other deck plates through a polyimide heat insulation mat with the thickness of 3 mm. The solar cell array 3 is installed on the outer side of the cabin plate through titanium alloy screws and polyimide heat insulation pads.
Fig. 6 is a telemetering curve of the temperature of the multifunctional structural battery on the rail, and fig. 7 is the temperature difference of the temperature measuring point of the structural battery. As can be seen from FIGS. 6 and 7, the temperature range of the multifunctional structural battery is 15.8-20.9 ℃, and the requirement of the working temperature of 10-35 ℃ is met. The temperature difference of the temperature measuring points is 4.50 ℃ at most, and the requirement of not more than 5 ℃ is met.
Although the present invention has been described in detail by the above-mentioned embodiments, it is not limited thereto. Various modifications and alterations may be made by those skilled in the art without departing from the spirit and scope of the invention, and the scope of the invention is accordingly to be determined by the appended claims.
Claims (10)
1. An active and passive comprehensive thermal control design method of a space multifunctional structure battery is characterized by comprising the following steps of S1-S5:
s1, inputting the configuration, heat consumption parameters and thermophysical parameters of the multifunctional structural battery;
the multifunctional structure battery comprises a battery supporting structure and a plurality of single batteries;
s2, carrying out distributed active control measure design: selecting a heat conduction pad and a heat conduction carbon fiber plate with a heat conductivity coefficient larger than a preset threshold value, arranging a plurality of temperature measurement loops and a plurality of temperature control loops on the heat conduction carbon fiber plate, 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 loops;
s3, carrying out passive thermal control measure design based on multi-stage temperature control: setting passive thermal control measures for the multifunctional structural battery from three levels of a component level, an assembly level and a whole star level, wherein the passive thermal control measures are used for realizing passive temperature control by setting any one or more of heat insulation materials, heat insulation devices and structural layouts;
s4, establishing a thermal analysis model of the multifunctional structural battery, setting boundary conditions of the multifunctional structural battery, and performing on-orbit working condition thermal analysis according to input parameters based on the thermal analysis model to obtain the temperature field distribution of the multifunctional structural battery;
s5, evaluating whether the temperature range and/or the temperature difference of the multifunctional structural battery obtained in the step S4 meet the index requirements, and if so, ending the design; if the temperature difference does not meet the index requirements, the arrangement forms of the temperature measuring loop and the temperature control loop are adjusted, the parameters of the temperature control logic are changed, the component-level passive heat insulation measures and the whole-star-level passive heat insulation measures are adjusted, and the steps S2 to S5 are executed again to redesign the thermal control scheme of the multifunctional structural battery until the temperature range and the temperature difference meet the index requirements.
2. The active and passive integrated thermal control design method of the aerospace multifunctional structure battery as claimed in claim 1, wherein the preset threshold value of the thermal conductivity of the thermal conductive carbon fiber plate in step S2 is 5W/mK; the heat conducting pad is arranged on the surface of the single battery and is positioned between the single battery and the heat conducting carbon fiber plate.
3. The active and passive integrated thermal control design method of the aerospace multifunctional structure battery as claimed in claim 1, wherein the heat conducting carbon fiber plate in step S2 is made of M-series carbon fibers; the heat conduction pad is made of flexible heat conduction materials, and the heat conduction coefficient of the heat conduction materials is larger than 5W/mK.
4. The active and passive integrated thermal control design method of the aerospace multifunctional structure battery as claimed in claim 1, wherein the temperature measurement loop in step S2 comprises a thermistor for temperature measurement and a thermal control lower computer for control, which are connected with each other; the temperature control loop comprises a heating sheet and a power supply which are connected with each other.
5. The active and passive integrated thermal control design method of the aerospace multifunctional structure battery according to claim 4, wherein the temperature control logic adopts a dual-compartment temperature control mode, and comprises: setting T to represent the temperature of the thermistor, delta T to represent the maximum allowable temperature difference, Tref to represent the temperature of the central area of the multifunctional structure battery, Tmin to represent the lower limit of a temperature control interval, Tmax to represent the upper limit of the temperature control interval, and when the temperature T of the thermistor for temperature measurement is lower than the lower limit of the temperature control interval, namely T < Tmin, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, namely T < Tref-delta T, starting the temperature control loop; and when the temperature T of the thermistor for measuring the temperature is higher than the upper limit of the temperature control interval, namely T is greater than Tmax, or the temperature difference value between the temperature T and the central area is greater than the maximum allowable temperature difference, namely T is greater than Tref + delta T, closing the temperature control loop.
6. The active and passive integrated thermal control design method for the aerospace multifunctional structure battery as claimed in any one of claims 1 to 5, wherein in the step S3, the component-level passive thermal insulation measures are as follows: when the multifunctional structure battery is integrated into the integrated cabin plate, a heat conduction material with the heat conductivity lower than a preset threshold value is filled between the multifunctional structure battery and the skin panel structure.
7. The active-passive integrated thermal control design method for the aerospace multifunctional structure battery according to any one of claims 1 to 5, wherein in the step S3, the module-level passive thermal insulation measure is as follows: the integrated cabin plate integrated by the multifunctional structure battery is coated with a plurality of layers of heat insulation materials, and any one or more than two of a heat insulation gasket, a heat insulation pad and a bolt with a heat insulation function are arranged at the connecting interface between the integrated cabin plate and other parts of the satellite body except the integrated cabin plate.
8. The active and passive integrated thermal control design method for the aerospace multifunctional structure battery according to any one of claims 1 to 5, wherein in the step S3, the whole star level passive thermal insulation measure is as follows: the configuration of the spacecraft and the layout of the solar cell array are optimized, and the position of the integrated cabin plate integrated by the multifunctional structural cell on the satellite body is adjusted, so that the cabin plate is prevented from directly receiving solar radiation or radiating to a cold and black space.
9. The active and passive integrated thermal control design method for the aerospace multifunctional structure battery according to any one of claims 1 to 5, wherein in the step S4, ANSYS software or UG software is adopted to establish a thermal analysis model of the multifunctional structure battery; the boundary condition of the multifunctional structural battery is specifically that the side surface of the integrated cabin plate containing the multifunctional structural battery is set to be at a constant temperature.
10. The active-passive integrated thermal control design method for the aerospace multifunctional structure battery according to any one of claims 1 to 5, wherein in the step S5, the parameters of the temperature control logic include any one or more than two of an upper limit of a temperature control interval, a lower limit of the temperature control interval and a maximum allowable temperature difference.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109708A (en) * | 2015-08-31 | 2015-12-02 | 北京航天长征飞行器研究所 | Thermal control method of spatial aircraft |
| WO2015180000A1 (en) * | 2014-05-26 | 2015-12-03 | 中国科学院长春光学精密机械与物理研究所 | Comprehensive management system for platform and payload integrated satellite |
| CN105955075A (en) * | 2016-05-10 | 2016-09-21 | 中国人民解放军国防科学技术大学 | Spacecraft in-orbit multifunctional structure integrated management and control system |
| CN105975712A (en) * | 2016-05-20 | 2016-09-28 | 南京航空航天大学 | Design optimization method for spacecraft passive thermal control parameters |
| CN106528976A (en) * | 2016-11-01 | 2017-03-22 | 中国人民解放军国防科学技术大学 | Integrated design method for multifunctional aerospace structure with force-power integration function |
| CN112257191A (en) * | 2020-12-23 | 2021-01-22 | 中国人民解放军国防科技大学 | Load platform integrated microsatellite thermal control subsystem optimization method and system |
| CN113060303A (en) * | 2021-03-18 | 2021-07-02 | 中国人民解放军国防科技大学 | Integrated spacecraft cabin plate containing structural lithium battery |
-
2021
- 2021-12-03 CN CN202111470590.0A patent/CN114154243A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015180000A1 (en) * | 2014-05-26 | 2015-12-03 | 中国科学院长春光学精密机械与物理研究所 | Comprehensive management system for platform and payload integrated satellite |
| CN105109708A (en) * | 2015-08-31 | 2015-12-02 | 北京航天长征飞行器研究所 | Thermal control method of spatial aircraft |
| CN105955075A (en) * | 2016-05-10 | 2016-09-21 | 中国人民解放军国防科学技术大学 | Spacecraft in-orbit multifunctional structure integrated management and control system |
| CN105975712A (en) * | 2016-05-20 | 2016-09-28 | 南京航空航天大学 | Design optimization method for spacecraft passive thermal control parameters |
| CN106528976A (en) * | 2016-11-01 | 2017-03-22 | 中国人民解放军国防科学技术大学 | Integrated design method for multifunctional aerospace structure with force-power integration function |
| CN112257191A (en) * | 2020-12-23 | 2021-01-22 | 中国人民解放军国防科技大学 | Load platform integrated microsatellite thermal control subsystem optimization method and system |
| CN113060303A (en) * | 2021-03-18 | 2021-07-02 | 中国人民解放军国防科技大学 | Integrated spacecraft cabin plate containing structural lithium battery |
Non-Patent Citations (2)
| Title |
|---|
| 丁延卫;付俊明;尤政;: "纳型卫星热控系统设计与仿真", 系统仿真学报, no. 01, 20 January 2006 (2006-01-20) * |
| 刘海娃;汤建华;: "浮动断接器热控设计与仿真", 火箭推进, no. 01, 15 February 2015 (2015-02-15) * |
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