CN116742183A - Heat management system for energy storage battery of pipe beam of near space vehicle - Google Patents
Heat management system for energy storage battery of pipe beam of near space vehicle Download PDFInfo
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- CN116742183A CN116742183A CN202210211893.9A CN202210211893A CN116742183A CN 116742183 A CN116742183 A CN 116742183A CN 202210211893 A CN202210211893 A CN 202210211893A CN 116742183 A CN116742183 A CN 116742183A
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- 238000004146 energy storage Methods 0.000 title claims abstract description 145
- 239000012528 membrane Substances 0.000 claims abstract description 54
- 238000007599 discharging Methods 0.000 claims abstract description 33
- 230000017525 heat dissipation Effects 0.000 claims description 43
- 239000006260 foam Substances 0.000 claims description 26
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 5
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 4
- 239000006261 foam material Substances 0.000 claims description 3
- 230000001737 promoting effect Effects 0.000 claims description 2
- 210000004027 cell Anatomy 0.000 claims 4
- 210000000352 storage cell Anatomy 0.000 claims 1
- 230000007613 environmental effect Effects 0.000 abstract description 6
- 238000009413 insulation Methods 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 24
- 238000004321 preservation Methods 0.000 description 14
- 238000010438 heat treatment Methods 0.000 description 11
- 238000000605 extraction Methods 0.000 description 10
- 239000000178 monomer Substances 0.000 description 5
- 239000011261 inert gas Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 239000004642 Polyimide Substances 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 229920001721 polyimide Polymers 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000005437 stratosphere Substances 0.000 description 1
Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/613—Cooling or keeping cold
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/62—Heating or cooling; Temperature control specially adapted for specific applications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/656—Means for temperature control structurally associated with the cells characterised by the type of heat-exchange fluid
- H01M10/6561—Gases
- H01M10/6563—Gases with forced flow, e.g. by blowers
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/658—Means for temperature control structurally associated with the cells by thermal insulation or shielding
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Secondary Cells (AREA)
Abstract
The application provides a heat management system of a tube beam energy storage battery of a near space vehicle, which comprises the following components: the device comprises an elastic inflatable film, an air charging and discharging device, an energy storage battery pack and an air discharging device, wherein the elastic inflatable film, the energy storage battery pack and the air discharging device are positioned in a wing tubular beam, and the energy storage battery pack is positioned in the elastic inflatable film; when the aircraft climbs, the temperature of the energy storage battery pack is higher than the normal working temperature, the elastic inflatable membrane is exhausted by the air charging and exhausting device, and the air exhausting device is started to radiate heat and cool the energy storage battery pack; when the temperature of the energy storage battery pack is reduced to a normal working temperature range, the air exhaust device is closed; when the aircraft flies at high altitude, the temperature of the energy storage battery pack is lower than the normal working temperature, the elastic inflatable membrane is inflated by the inflation and deflation device, and the energy storage battery pack is subjected to heat insulation by closing the inflation and deflation device. By applying the technical scheme of the application, the technical problem of insufficient flying performance caused by the fact that the adjacent space vehicle improves the environmental adaptability of the energy storage battery in the prior art can be solved.
Description
Technical Field
The application relates to the technical field of aerospace aircrafts, in particular to a heat management system for an energy storage battery of a tube beam of a near-space aircraft.
Background
The solar unmanned aerial vehicle energy system mainly comprises a solar energy collecting device and an energy storage battery, wherein the technical level of the energy storage battery directly determines the amount of energy which can be stored and utilized by the solar unmanned aerial vehicle, and is a key technology for realizing the day and night continuous flight of the solar unmanned aerial vehicle. Most solar energy aircraft energy storage batteries adopt lithium ion batteries, and if high specific energy batteries are adopted, the energy-to-weight ratio of the solar energy aircraft energy storage batteries is greatly improved, and the flight endurance and performance of the aircraft are improved. When the solar unmanned aerial vehicle flies at low altitude in daytime, the climbing power is high, the discharge multiplying power of the energy storage battery is high, the low-altitude environment temperature is high, a large amount of heat is generated when the high-energy-weight ratio energy storage battery works at high power, and heat dissipation measures are needed; when the stratosphere flies at night, the ambient temperature of the energy storage battery is about-55 ℃ at the lowest, and heat preservation and heating measures are needed. If no temperature control measures are taken, the performance of the energy storage battery is reduced, even the energy storage battery is out of control, so that the solar unmanned aerial vehicle and other nearby spaces or high-altitude aircrafts adopting the energy storage battery are required to consider the environmental adaptability of the energy storage battery so as to improve the thermal characteristics of the battery.
The solar unmanned aerial vehicle for long voyage in the near space reduces aerodynamic drag, generally adopts a low-wing-load high-aspect-ratio configuration, has poor structural rigidity due to large wing span, and has large wing deformation in the flight process, and if the structural rigidity of the wing is unilaterally improved, the total weight of the unmanned aerial vehicle is increased, so that the unmanned aerial vehicle is unfavorable for long voyage flight. The structural weight of the solar unmanned aerial vehicle and the weight of the energy system account for more than 60% of the weight of the whole unmanned aerial vehicle, and if the weight of the two parts is reasonably utilized in the overall design, the performance of the aircraft platform is greatly improved.
The conventional solar unmanned aerial vehicle arranges the energy storage battery in a power nacelle or a fuselage of the front edge of the wing, the exterior of the battery is covered with PMI foam for heat preservation, and the exterior of the foam is required to be covered with a layer of hard shell for protecting the battery. The energy storage battery scheme can generate redundant structural weight, and the endurance and range of the solar energy aircraft are greatly dependent on energy and weight, so that the arrangement form is unfavorable for improving the flight performance of the solar unmanned aerial vehicle. Therefore, there is a need for a tubular beam-energy storage battery thermal management system that facilitates wing load shedding, increases the energy storage battery envelope weight ratio, and reduces the overall weight of the unmanned aerial vehicle.
Disclosure of Invention
The present application aims to solve at least one of the technical problems existing in the prior art.
The application provides a heat management system of a tube beam energy storage battery of a near-space aircraft, which comprises the following components: the device comprises an elastic inflatable membrane, an air charging and discharging device, an energy storage battery pack and an air discharging device, wherein the elastic inflatable membrane, the energy storage battery pack and the air discharging device are positioned in a wing tubular beam of an adjacent space vehicle; when the aircraft climbs, the temperature of the energy storage battery pack is higher than the normal working temperature, the elastic inflatable membrane is exhausted by the air charging and exhausting device, and the air exhausting device is started to radiate heat and cool the energy storage battery pack; when the temperature of the energy storage battery pack is reduced to a normal working temperature range, the air exhaust device is closed; when the aircraft flies at high altitude, the temperature of the energy storage battery pack is lower than the normal working temperature, the elastic inflatable membrane is inflated by the inflation and deflation device, and the energy storage battery pack is subjected to heat insulation by closing the inflation and deflation device.
Further, the elastic inflatable film employs a high-strength rubber film.
Further, the inflation and deflation device comprises a gas cylinder and an air extraction device, the gas cylinder and the air extraction device are respectively connected with the elastic inflatable membrane in an airtight mode, gas is stored in the gas cylinder to inflate the elastic inflatable membrane, and the air extraction device is used for exhausting the elastic inflatable membrane.
Further, inert gas is used as the gas stored in the gas cylinder.
Further, the exhaust device comprises two fans, wherein the two fans are axially positioned on two sides of the energy storage battery pack along the pipe beam, one fan is used for sucking air into the pipe beam, and the other fan is used for exhausting air out of the pipe beam.
Further, the energy storage battery pack includes: the battery array and the external heat dissipation plate are positioned on the first side face and/or the second side face of the battery array, and the first side face is opposite to the second side face.
Further, the energy storage battery pack also comprises a foam fixing plate, the foam fixing plate is located on a third side face and a fourth side face of the battery array, the third side face and the fourth side face are oppositely arranged, and the energy storage battery pack is fixedly extruded with the inner wall of the tubular beam through the foam fixing plate.
Further, the foam fixing plate is prepared by adopting PMI foam.
Further, the battery array comprises a plurality of battery packs, the plurality of battery packs are stacked, any battery pack comprises a battery cell, an internal heat dissipation plate and an elastic plate, and the battery cell is located between the internal heat dissipation plate and the elastic plate.
Further, the elastic plate is made of foam materials.
Further, the inner heat dissipation plate is provided with a concave cavity, the battery cells are located in the concave cavity of the inner heat dissipation plate, and the plurality of inner heat dissipation plates are in contact with the outer heat dissipation plate.
Further, the external heat dissipation plate and the internal heat dissipation plate are aluminum plates.
Further, any one of the battery packs further includes a temperature sensor located between the battery cell and the elastic plate.
Further, the energy storage battery pack further comprises a fixing band, and the fixing band is arranged around the battery array and the foam fixing plate.
Further, the energy storage battery pack further comprises a BMS, wherein the BMS is located on the fifth side face of the battery array and is connected with the battery array, the air charging and discharging device and the air discharging device respectively.
By the aid of the technical scheme, the heat management system for the energy storage battery of the pipe beam of the near-space aircraft is provided, the energy storage battery pack is arranged in the pipe beam, load can be relieved for the spar, meanwhile, the pipe beam structure is utilized for heat preservation and heat dissipation of the energy storage battery pack, and the elastic inflatable film and the exhaust device work cooperatively to achieve rapid heat dissipation and heat insulation and heat preservation of the energy storage battery pack. The application has simple and convenient structural design, better thermal control and reliability, can meet the heat dissipation and heat preservation requirements of the flying of the near space aircraft during long voyage, and simultaneously meets the light-weight requirement of the aircraft. Compared with the prior art, the technical scheme of the application can solve the technical problem that the flying performance is insufficient due to the fact that the adjacent space vehicle improves the environmental adaptability of the energy storage battery in the prior art.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application. It is evident that the drawings in the following description are only some embodiments of the present application and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 illustrates a schematic installation of a near space vehicle tubular beam energy storage battery thermal management system provided in accordance with an embodiment of the present application;
fig. 2 illustrates a first side view of an energy storage battery pack provided in accordance with a specific embodiment of the present application;
fig. 3 illustrates a second side view of an energy storage battery pack provided in accordance with an embodiment of the present application;
fig. 4 is a schematic view showing the structure of a battery array according to an embodiment of the present application;
fig. 5 shows a schematic installation view of an energy storage battery pack and an air charging and discharging device in a tubular beam according to an embodiment of the present application.
Wherein the above figures include the following reference numerals:
1: a tubular beam; 2: a fan; 3: an internal heat dissipation plate; 4: an external heat dissipation plate; 5: BMS;6: a battery cell; 7: a fixing belt; 8: a foam fixing plate; 9: an elastic plate; 10: a temperature sensor; 11: an energy storage battery pack; 12: an elastically inflatable membrane; 13: and an air charging and discharging device.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in fig. 1 to 5, there is provided a heat management system for a tube beam energy storage battery of a spacecraft, according to an embodiment of the present application, the heat management system comprising: the device comprises an elastic inflatable membrane 12, an air charging and discharging device 13, an energy storage battery pack 11 and an air discharging device, wherein the elastic inflatable membrane 12, the energy storage battery pack 11 and the air discharging device are positioned in a wing tubular beam 1 of an adjacent space vehicle, the energy storage battery pack 11 is positioned in the elastic inflatable membrane 12, the air charging and discharging device 13 is connected with the elastic inflatable membrane 12 to charge and discharge the elastic inflatable membrane 12, and the air discharging device is used for promoting air circulation in the tubular beam 1; when the aircraft climbs, the temperature of the energy storage battery pack 11 is higher than the normal working temperature, the elastic inflatable membrane 12 is exhausted by the air charging and exhausting device 13, and the air exhausting device is started to radiate heat and cool the energy storage battery pack 11; when the temperature of the energy storage battery pack 11 is reduced to a normal working temperature range, the air exhaust device is closed; when the aircraft flies high, the temperature of the energy storage battery pack 11 is lower than the normal working temperature, the elastic inflatable membrane 12 is inflated by the inflation and deflation device 13, and the air exhaust device is closed to insulate heat and preserve heat of the energy storage battery pack 11.
By means of the configuration mode, the heat management system for the energy storage battery of the pipe beam of the near space aircraft is provided, the energy storage battery pack 11 is arranged in the pipe beam 1, load can be relieved for the spar, meanwhile, the heat preservation and the heat dissipation of the energy storage battery pack 11 can be carried out by utilizing the pipe beam 1 structure, and the rapid heat dissipation and the heat insulation and the heat preservation of the energy storage battery pack 11 can be realized through the cooperative work of the elastic inflatable membrane 12 and the exhaust device. The application has simple and convenient structural design, better thermal control and reliability, can meet the heat dissipation and heat preservation requirements of the flying of the near space aircraft during long voyage, and simultaneously meets the light-weight requirement of the aircraft. Compared with the prior art, the technical scheme of the application can solve the technical problem that the flying performance is insufficient due to the fact that the adjacent space vehicle improves the environmental adaptability of the energy storage battery in the prior art.
As an embodiment of the present application, the elastomeric inflatable membrane 12 may be a high strength rubber membrane. The high-strength rubber membrane can be inflated and deflated like a balloon, the energy storage battery pack 11 is wrapped by the high-strength rubber membrane and placed inside the high-strength rubber membrane, and inflation and deflation of the high-strength rubber membrane can be achieved through the inflation and deflation device 13. After inflation is complete, the gas within the elastomeric inflatable membrane 12 is substantially no longer flowing, and the gas within the elastomeric inflatable membrane 12 is now thermally insulated. After the exhaust is completed, the elastic inflatable membrane 12 is tightly attached to the outer wall of the energy storage battery pack 11, so that the energy storage battery pack 11 is favorable for heat dissipation; if the exhaust device is started at this time, the exhaust device drives the gas in the tubular beam 1 to flow, and the energy storage battery pack 11 can be rapidly cooled.
Further, in the present application, the configurable inflatable device 13 includes a gas cylinder and a gas extraction device, the gas cylinder and the gas extraction device are respectively connected with the elastic inflatable membrane 12 in a gas-tight manner, the gas cylinder stores gas to inflate the elastic inflatable membrane 12, and the gas extraction device is used to exhaust the elastic inflatable membrane 12. As an embodiment of the present application, the gas stored in the gas cylinder may be inert gas. The air extraction equipment can be connected with the air bottle so as to recharge the extracted inert gas into the air bottle, thereby realizing the recycling of the inert gas. The charging and discharging device 13 can be arranged outside the wing tubular beam 1.
In addition, in order to improve the heat dissipation performance of the thermal management system of the energy storage battery, as shown in fig. 1, the configurable air exhaust device includes two fans 2, wherein the two fans 2 are located at two sides of the energy storage battery pack 11 along the axial direction of the tubular beam 1, one fan is used for sucking air into the tubular beam 1, and the other fan is used for exhausting air out of the tubular beam 1. Through the air suction fan and the exhaust fan which are arranged on two sides of the energy storage battery pack 11, forced convection can be formed in the tubular beam 1, and the heat exchange effect of the energy storage battery pack 11 is enhanced. As an embodiment of the application, two fans 2 may be placed at a distance from the energy storage battery pack 11. The number of fans can be increased according to the heat dissipation requirement, and the types of the fans can be adjusted.
Further, in the present application, in order to further improve the heat dissipation of the energy storage battery pack 11, as shown in fig. 2 and 3, the configurable energy storage battery pack 11 includes: the battery array and the outside heating panel 4, outside heating panel 4 is located the first side and/or the second side of battery array, and first side and second side are opposite to each other and set up. The battery array can be effectively radiated and balanced in temperature difference through the external radiating plate 4. As an embodiment of the present application, the external heat dissipation plate 4 may be an aluminum plate.
In addition, in the present application, in order to maintain stable installation of the energy storage battery pack 11 in the tubular beam 1 while leaving a margin for expansion of the batteries in the energy storage battery pack 11, as shown in fig. 2 and 3, the configurable energy storage battery pack 11 further includes foam fixing plates 8, the foam fixing plates 8 being located at a third side and a fourth side of the battery array, the third side being disposed opposite to the fourth side, and the energy storage battery pack 11 being press-fixed with the inner wall of the tubular beam 1 by the foam fixing plates 8. In the present application, the elastic inflatable membrane 12 wraps the energy storage battery pack 11, and the energy storage battery pack 11 is pressed and fixed with the inner wall of the tubular beam 1 through the foam fixing plate 8, as shown in fig. 5, no matter the elastic inflatable membrane 12 is in an inflated or deflated state. The foam fixing plate 8 has a certain compression amount, so that not only can the compression fixing with buffering be provided for the energy storage battery pack 11, but also a certain space can be provided for the expansion of the battery in the energy storage battery pack 11 at a high temperature. As a specific example of the present application, the foam fixing plate 8 may be prepared using PMI (polymethacrylimide) foam or a shock absorbing buffer material. The outer side of the foam fixing plate 8 and the inner wall of the tubular beam 1 are designed along with each other, and the specific size of the foam fixing plate 8 can be designed according to practical situations.
Further, in the present application, in order to increase the voltage range of the energy storage battery pack 11, to adapt to the energy demand of the aircraft, as shown in fig. 2 to 4, the configurable battery array includes a plurality of battery packs, and the plurality of battery packs are stacked, and any one of the battery packs includes a battery cell 6, an internal heat dissipation plate 3, and an elastic plate 9, and the battery cell 6 is located between the internal heat dissipation plate 3 and the elastic plate 9. Inside heating panel 3 and battery monomer 6 direct contact can accelerate the export to battery monomer 6 inside heat through inside heating panel 3, and elastic plate 9 can provide the reservation expansion space for battery monomer 6.
As an embodiment of the present application, the inner heat dissipation plate 3 may be an aluminum plate, and the elastic plate 9 may be made of foam material. The specific dimensions of the elastic plate 9 can be designed according to the actual situation. The number of battery packs can be set according to actual flight requirements, as shown in fig. 4, the battery array can comprise 12 battery packs, the voltage range of the battery packs is 3-4.2V, and the lugs of the 12 battery packs are connected in parallel, so that the overall voltage range of the energy storage battery pack 11 is 36-50.4V.
In addition, in the present application, in order to further accelerate the heat conduction from the inside of the battery cell 6, the inside heat dissipation plate 3 may be provided with a cavity, the battery cell 6 is located in the cavity of the inside heat dissipation plate 3, and the plurality of inside heat dissipation plates 3 are in contact with the outside heat dissipation plate 4. Through setting up a plurality of inside heating panel 3 and outside heating panel 4 contact, can pass through inside heating panel 3 and outside heating panel 4 in proper order with battery monomer 6 and transmit the energy storage battery package 11 outside on the one hand for the heat dissipation cooling of energy storage battery package 11, on the other hand can equalize the difference in temperature between a plurality of battery unit, avoid single battery temperature too high or too low, and then promote energy storage battery's output performance. As an embodiment of the present application, as shown in fig. 4, the cross section of the inner heat dissipation plate 3 is "[", and the battery cell 6 is located in the cavity. A plurality of surfaces of the battery cell 6 may be disposed in contact with the internal heat dissipation plate 3 to improve heat dissipation efficiency.
Further, in the present application, in order to obtain the accurate temperature of the battery cell 6, as shown in fig. 4, any battery pack may be configured to further include a temperature sensor 10, the temperature sensor 10 being located between the battery cell 6 and the elastic plate 9. The surface temperature of each battery cell 6 can be monitored in real time through the temperature sensor 10, and then the energy storage battery pack 11 can be timely cooled or insulated.
In addition, in the present application, in order to reduce the weight of the energy storage battery pack 11, as shown in fig. 2 and 3, the configurable energy storage battery pack 11 further includes a fixing strap 7, the fixing strap 7 being disposed around the battery array and the foam fixing plate 8. The fastening of a plurality of battery packs and foam fixed plates 8 in the battery array can be realized through the fixed belt 7, so that the use of a shell and a supporting structure is avoided, the requirements of light weight and simplification can be met, the load shedding of the wing is facilitated, the energy-to-weight ratio of the energy storage battery pack 11 is improved, and the overall weight of the aircraft is further reduced. As an embodiment of the present application, the fixing tape 7 may be a polyimide tape.
Further, in the present application, in order to realize monitoring of the battery voltage, current and temperature, as shown in fig. 2 and 3, the configurable energy storage battery pack 11 further includes a BMS5 (Battery Management System ), the BMS5 is located at a fifth side of the battery array, and the BMS5 is connected to the battery array, the air charging and discharging device 13 and the air discharging device, respectively. The battery array, the air charging and discharging device 13 and the air discharging device can be monitored and controlled in real time through the BMS5, and the temperature of the energy storage battery pack 11 can be adjusted in time. As a specific embodiment of the present application, the BMS5 is respectively connected to the plurality of battery cells 6, the plurality of temperature sensors 10, the air cylinder and the air pumping device, and the two fans 2 in the battery array, and the BMS5 can control the air cylinder and the air pumping device, and the two fans 2 according to the real-time temperature of the battery cells 6 measured by the temperature sensors 10, so as to effectively dissipate heat or insulate heat of the plurality of battery cells 6.
By adopting the configuration mode, when the aircraft climbs, the discharge power of the energy storage battery pack 11 is larger, the heat release amount is larger, when the temperature sensor 10 monitors that the temperature of the battery cell 6 is higher than the normal working temperature, the BMS5 controls the air extraction equipment to exhaust the elastic inflatable membrane 12, and the elastic inflatable membrane 12 is tightly attached to the outer wall of the energy storage battery pack 11 after the air exhaust is completed; meanwhile, the BMS5 controls the two fans 2 to be automatically turned on, forced convection is formed in the circular tube beam 1, wind flows into the tube beam 1 through one fan 2, flows through the two external heat dissipation aluminum plates on the side surface of the energy storage battery pack 11 through the elastic inflatable membrane 12 to the other fan 2 to flow out, and at the moment, the air plays a role of a heat exchange medium. When the temperature sensor 10 detects that the temperature of the battery cell 6 is in the normal working temperature range, the BMS5 controls the fan 2 to be turned off, and air in the circular tube beam 1 does not basically flow at the moment, and the air can play a role in heat insulation and heat preservation. When the aircraft flies at high altitude, the minimum external temperature can reach-55 ℃, at the moment, the energy storage battery pack 11 is in a high altitude low temperature environment, the temperature sensor 10 collects that the temperature of the battery monomer 6 is lower than the normal working temperature, the BMS5 controls the gas cylinder to charge the elastic inflatable membrane 12, gas in the elastic inflatable membrane 12 does not flow any more after the inflation is completed, the internal gas further has a heat preservation effect, and the temperature of the energy storage battery is guaranteed to be at the normal working temperature.
The heat management system for the pipe beam energy storage battery of the near space aircraft is simple and convenient in design, has good heat control performance and reliability, meets the heat dissipation and heat preservation requirements of the near space aircraft in long voyage, and does not have unified environmental control requirements on the aircraft. The application can reasonably utilize the structure to reduce the total weight of the whole machine, and utilizes the reasonable layout of the energy storage battery pack 11 in the tubular beam 1 to achieve the effect of reducing the load on the wing, thereby further reducing the weight ratio of the structure.
For a further understanding of the present application, the present application is described in detail below with reference to fig. 1-5 for a heat management system for a spacecraft tubular beam energy storage battery.
As shown in fig. 1 to 5, there is provided a heat management system for a tube beam energy storage battery of a spacecraft, according to an embodiment of the present application, the heat management system comprising: an elastic inflatable membrane 12, a gas cylinder, an air extraction device, two fans 2 and an energy storage battery pack 11. The elastic inflatable membrane 12, the two fans 2 and the energy storage battery pack 11 are located in the wing tubular beam 1 of the near-space aircraft, the energy storage battery pack 11 is located in the elastic inflatable membrane 12, gas is stored in the gas cylinder to inflate the elastic inflatable membrane 12, the air extraction equipment is used for exhausting the elastic inflatable membrane 12, the two fans 2 are located on two sides of the energy storage battery pack 11 along the tubular beam 1 in the axial direction, one fan is used for sucking air into the tubular beam 1, and the other fan is used for exhausting air out of the tubular beam 1.
The energy storage battery pack 11 includes: the battery array, outside heating panel 4, foam fixed plate 8, fixed band 7 and BMS5, outside heating panel 4 are located battery array's first side and/or second side, and foam fixed plate 8 is located battery array's third side and fourth side, and energy storage battery package 11 is fixed with tubular beam 1 inner wall extrusion through foam fixed plate 8, and fixed band 7 encircles battery array and foam fixed plate 8 setting. The BMS5 is positioned on the fifth side of the battery array, and the BMS5 is respectively connected with the battery array, the air charging and discharging device 13 and the air discharging device.
The battery array comprises a plurality of battery packs, the plurality of battery packs are stacked, any battery pack comprises a battery cell 6, an internal heat dissipation plate 3, a temperature sensor 10 and an elastic plate 9, the battery cell 6 is located between the internal heat dissipation plate 3 and the elastic plate 9, and the temperature sensor 10 is located between the battery cell 6 and the elastic plate 9.
In summary, the application provides a heat management system for an energy storage battery of a tube beam of a near space aircraft, which is capable of reducing load of a spar and simultaneously utilizing a tube beam structure to perform heat preservation and heat dissipation on the energy storage battery pack by arranging the energy storage battery pack in the tube beam, and realizing rapid heat dissipation and heat insulation and heat preservation of the energy storage battery pack by cooperative work of an elastic inflatable film and an exhaust device. The application has simple and convenient structural design, better thermal control and reliability, can meet the heat dissipation and heat preservation requirements of the flying of the near space aircraft during long voyage, and simultaneously meets the light-weight requirement of the aircraft. Compared with the prior art, the technical scheme of the application can solve the technical problem that the flying performance is insufficient due to the fact that the adjacent space vehicle improves the environmental adaptability of the energy storage battery in the prior art.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present application.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (15)
1. A near space vehicle tubular beam energy storage battery thermal management system, the near space vehicle tubular beam energy storage battery thermal management system comprising: the device comprises an elastic inflatable membrane (12), an air charging and discharging device (13), an energy storage battery pack (11) and an air discharging device, wherein the elastic inflatable membrane (12), the energy storage battery pack (11) and the air discharging device are positioned in a wing tubular beam (1) of an adjacent space vehicle, the energy storage battery pack (11) is positioned in the elastic inflatable membrane (12), the air charging and discharging device (13) is connected with the elastic inflatable membrane (12) to charge and discharge air to the elastic inflatable membrane (12), and the air discharging device is used for promoting air circulation in the tubular beam (1); when the aircraft climbs, the temperature of the energy storage battery pack (11) is higher than the normal working temperature, the elastic inflatable membrane (12) is exhausted by the air charging and exhausting device (13), and the air exhausting device is started to radiate heat and cool the energy storage battery pack (11); when the temperature of the energy storage battery pack (11) is reduced to a normal working temperature range, the air exhaust device is closed; when the aircraft flies at high altitude, the temperature of the energy storage battery pack (11) is lower than the normal working temperature, the air charging and discharging device (13) charges the elastic inflatable membrane (12), and the air discharging device is closed to insulate heat and preserve heat of the energy storage battery pack (11).
2. The spacecraft tubular beam energy storage battery thermal management system of claim 1, wherein said elastomeric inflatable membrane (12) is a high strength rubber membrane.
3. The heat management system of a tube beam energy storage battery of a spacecraft of claim 1, wherein said air charging and discharging device (13) comprises an air cylinder and an air extracting device, said air cylinder and said air extracting device are respectively connected with said elastic inflatable membrane (12) in an airtight manner, said air cylinder stores air to charge said elastic inflatable membrane (12), said air extracting device is used for discharging said elastic inflatable membrane (12).
4. The system of claim 3, wherein the gas stored in the gas cylinder is inert.
5. The heat management system for the energy storage battery of the pipe beam of the near space vehicle according to claim 1, wherein the exhaust device comprises two fans (2), the two fans (2) are axially arranged on two sides of the energy storage battery pack (11) along the pipe beam (1), one fan is used for sucking air into the pipe beam (1), and the other fan is used for exhausting air out of the pipe beam (1).
6. The spacecraft tubular beam energy storage battery thermal management system of claim 1, wherein said energy storage battery package (11) comprises: the battery pack comprises a battery array and an external heat dissipation plate (4), wherein the external heat dissipation plate (4) is positioned on a first side face and/or a second side face of the battery array, and the first side face is opposite to the second side face.
7. The heat management system of an energy storage battery of a tubular beam of a spacecraft of claim 6, wherein the energy storage battery pack (11) further comprises foam fixing plates (8), the foam fixing plates (8) are located on a third side face and a fourth side face of the battery array, the third side face is opposite to the fourth side face, and the energy storage battery pack (11) is fixed with the inner wall of the tubular beam (1) through the foam fixing plates (8) in a pressing mode.
8. The heat management system of a tube beam energy storage battery for a spacecraft of claim 7, wherein said foam fixture plate (8) is made of PMI foam.
9. The heat management system of a tube beam energy storage battery of a spacecraft of any of claims 6 to 8, wherein said battery array comprises a plurality of battery packs, said plurality of battery packs being stacked, any battery pack comprising a battery cell (6), an inner heat dissipating plate (3) and a resilient plate (9), said battery cell (6) being located between said inner heat dissipating plate (3) and said resilient plate (9).
10. The heat management system of a tube beam energy storage cell of a spacecraft of claim 9, wherein said elastic sheet (9) is made of foam material.
11. The heat management system of a tube beam energy storage battery of a spacecraft of claim 9, wherein said inner heat spreader plate (3) has a cavity, said battery cells (6) are positioned within said cavity of said inner heat spreader plate (3), and a plurality of inner heat spreader plates (3) are in contact with an outer heat spreader plate (4).
12. The heat management system of a tube beam energy storage battery of a spacecraft of claim 9, wherein said outer heat spreader plate (4) and said inner heat spreader plate (3) are aluminum plates.
13. The spacecraft tubular beam energy storage battery thermal management system of claim 9, wherein either battery pack further comprises a temperature sensor (10), said temperature sensor (10) being located between said battery cells (6) and said elastic plate (9).
14. The spacecraft tubular beam energy storage battery thermal management system of claim 7, wherein said energy storage battery package (11) further comprises a securing strap (7), said securing strap (7) being disposed around said battery array and said foam securing plate (8).
15. The spacecraft tubular beam energy storage battery thermal management system of any of claims 6 to 14, wherein said energy storage battery package (11) further comprises a BMS (5), said BMS (5) being located at a fifth side of a battery array, said BMS (5) being connected to said battery array, said charging and discharging means (13) and said discharging means, respectively.
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|---|---|---|---|
| CN202210211893.9A CN116742183A (en) | 2022-03-04 | 2022-03-04 | Heat management system for energy storage battery of pipe beam of near space vehicle |
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| CN202210211893.9A CN116742183A (en) | 2022-03-04 | 2022-03-04 | Heat management system for energy storage battery of pipe beam of near space vehicle |
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