Near-space vehicle tubular beam energy storage battery thermal management system

Abstract

This invention provides a thermal management system for a near-space vehicle's wing-span energy storage battery, comprising: an elastic inflatable membrane, an inflation / deflation device, an energy storage battery pack, and a ventilation device. The elastic inflatable membrane, energy storage battery pack, and ventilation device are located within the wing-span, with the energy storage battery pack situated within the elastic inflatable membrane. During flight climb, when the energy storage battery pack temperature exceeds the normal operating temperature, the inflation / deflation device vents air from the elastic inflatable membrane, and the ventilation device activates to cool the energy storage battery pack. When the energy storage battery pack temperature drops to the normal operating temperature range, the ventilation device shuts off. During high-altitude flight, when the energy storage battery pack temperature falls below the normal operating temperature, the inflation / deflation device inflates the elastic inflatable membrane, and the ventilation device shuts off to insulate the energy storage battery pack. Applying this invention solves the technical problem of insufficient flight performance in near-space vehicles due to prior art efforts to improve the environmental adaptability of energy storage batteries.

Description

Technical Field

[0001] This invention relates to the field of aerospace vehicle technology, and in particular to a thermal management system for a near-space vehicle tubular beam energy storage battery. Background Technology

[0002] The energy system of a solar-powered drone mainly consists of a solar energy collection device and an energy storage battery. The level of energy storage battery technology directly determines the amount of energy that the solar-powered drone can store and utilize, and is a key technology for enabling continuous day and night flight. Most solar-powered aircraft use lithium-ion batteries for their energy storage. Using high-energy-density batteries will greatly increase their energy-to-weight ratio, improving the aircraft's flight time and performance. During daytime low-altitude flight, solar-powered drones have high climb power and high battery discharge rates. The high ambient temperature at low altitudes means that high-energy-density batteries will generate a large amount of heat when operating at high power, requiring heat dissipation measures. During nighttime stratospheric flight, the ambient temperature of the energy storage battery can drop to around -55°C, necessitating insulation and heating measures. Without temperature control, the performance of the energy storage battery will degrade, and even thermal runaway may occur. Therefore, solar-powered drones and other near-space or high-altitude aircraft using energy storage batteries must consider the environmental adaptability of the batteries to improve their thermal characteristics.

[0003] Near-space long-endurance solar-powered unmanned aerial vehicles (UAVs) typically employ a low wing loading and high aspect ratio configuration to reduce aerodynamic drag. However, this large wingspan results in poor structural rigidity and significant wing deformation during flight. Simply increasing the wing's structural rigidity would increase the overall weight of the UAV, hindering its long-endurance flight. The structural weight plus the energy system weight of a solar-powered UAV accounts for over 60% of its total weight. Properly utilizing these two weight components in the overall design will significantly improve the platform's performance.

[0004] Conventional solar-powered drones house energy storage batteries in the power nacelle on the leading edge of the wing or within the fuselage, covered with PMI foam for insulation. This foam is then protected by a rigid outer shell. This energy storage battery approach generates unnecessary structural weight, and since the flight time and range of a solar-powered aircraft largely depend on energy and weight, this arrangement is detrimental to improving the flight performance of solar-powered drones. Therefore, there is an urgent need for a tubular beam-energy storage battery thermal management system. This approach helps reduce wing load, improves the energy-to-weight ratio of the energy storage battery pack, and thus reduces the overall weight of the drone. Summary of the Invention

[0005] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0006] This invention provides a thermal management system for a near-space vehicle wing-spar energy storage battery. The system includes: an elastic inflatable membrane, an inflation / deflation device, an energy storage battery pack, and a ventilation device. The elastic inflatable membrane, energy storage battery pack, and ventilation device are located within the wing-spar of the near-space vehicle. The energy storage battery pack is located within the elastic inflatable membrane. The inflation / deflation device is connected to the elastic inflatable membrane to inflate and deflate it. The ventilation device promotes gas flow within the wing-spar. Specifically, when the vehicle climbs, if the energy storage battery pack temperature is higher than the normal operating temperature, the inflation / deflation device deflates the elastic inflatable membrane, and the ventilation device activates to cool the energy storage battery pack. When the energy storage battery pack temperature drops to the normal operating temperature range, the ventilation device closes. When the vehicle flies at high altitude, if the energy storage battery pack temperature is lower than the normal operating temperature, the inflation / deflation device inflates the elastic inflatable membrane, and the ventilation device closes to insulate the energy storage battery pack.

[0007] Furthermore, the elastic inflatable membrane is made of high-strength rubber.

[0008] Furthermore, the inflation / deflation device includes a gas cylinder and a pumping device, which are respectively airtightly connected to the elastic inflatable membrane. The gas cylinder stores gas to inflate the elastic inflatable membrane, and the pumping device is used to deflate the elastic inflatable membrane.

[0009] Furthermore, the gas stored in the cylinder is an inert gas.

[0010] Furthermore, the exhaust device includes two fans located on both sides of the energy storage battery pack along the axial direction of the tube beam. One fan is used to draw air into the tube beam, and the other fan is used to exhaust air out of the tube beam.

[0011] Furthermore, the energy storage battery pack includes: a battery array and an external heat sink, the external heat sink being located on a first side and / or a second side of the battery array, the first side being disposed opposite to the second side.

[0012] Furthermore, the energy storage battery pack also includes foam fixing plates, which are located on the third and fourth sides of the battery array. The third and fourth sides are arranged opposite to each other, and the energy storage battery pack is fixed to the inner wall of the tube beam by the foam fixing plates.

[0013] Furthermore, the foam fixing board is made of PMI foam.

[0014] Furthermore, the battery array includes multiple battery packs stacked together. Each battery pack includes a battery cell, an internal heat sink, and an elastic plate, with the battery cell located between the internal heat sink and the elastic plate.

[0015] Furthermore, the elastic board is made of foam material.

[0016] Furthermore, the internal heat sink has a cavity, the battery cell is located in the cavity of the internal heat sink, and multiple internal heat sinks are in contact with the external heat sink.

[0017] Furthermore, both the external and internal heat sinks are made of aluminum.

[0018] Furthermore, any battery pack also includes a temperature sensor located between the individual battery cells and the elastic plate.

[0019] Furthermore, the energy storage battery pack also includes a retaining strap that surrounds the battery array and the foam retaining plate.

[0020] Furthermore, the energy storage battery pack also includes a BMS, which is located on the fifth side of the battery array and is connected to the battery array, the charging and discharging device, and the ventilation device.

[0021] This invention provides a thermal management system for a near-space vehicle's tubular beam energy storage battery. This system, by housing the energy storage battery pack within the tubular beam, reduces the load on the wing spars while simultaneously using the beam structure for insulation and heat dissipation. Rapid heat dissipation and thermal insulation of the battery pack are achieved through the coordinated operation of an elastic inflatable membrane and an exhaust system. This invention features a simple and convenient structural design, good thermal control and reliability, and can meet the heat dissipation and insulation requirements of long-endurance near-space vehicles, while also satisfying the need for lightweight design. Compared with existing technologies, this invention solves the technical problem of insufficient flight performance in near-space vehicles due to efforts to improve the environmental adaptability of energy storage batteries. Attached Figure Description

[0022] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0023] Figure 1 An installation schematic diagram of a near-space vehicle tubular beam energy storage battery thermal management system according to a specific embodiment of the present invention is shown;

[0024] Figure 2 A first side view of an energy storage battery pack provided according to a specific embodiment of the present invention is shown;

[0025] Figure 3 A second side view of an energy storage battery pack provided according to a specific embodiment of the present invention is shown;

[0026] Figure 4 A schematic diagram of the structure of a battery array according to a specific embodiment of the present invention is shown;

[0027] Figure 5 A schematic diagram of the installation of an energy storage battery pack and a charging / discharging device within a tube beam, according to a specific embodiment of the present invention, is shown.

[0028] The above figures include the following reference numerals:

[0029] 1: Tube beam; 2: Fan; 3: Internal heat sink; 4: External heat sink; 5: BMS; 6: Battery cell; 7: Fixing strap; 8: Foam fixing plate; 9: Elastic plate; 10: Temperature sensor; 11: Energy storage battery pack; 12: Elastic inflatable membrane; 13: Inflation and deflation device. Detailed Implementation

[0030] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0032] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0033] like Figures 1 to 5 As shown in the figure, a thermal management system for a near-space vehicle wing spar energy storage battery is provided according to a specific embodiment of the present invention. The thermal management system includes: an elastic inflatable membrane 12, an inflation / deflation device 13, an energy storage battery pack 11, and a ventilation device. The elastic inflatable membrane 12, the energy storage battery pack 11, and the ventilation device are located within the wing spar 1 of the near-space vehicle. The energy storage battery pack 11 is located within the elastic inflatable membrane 12. The inflation / deflation device 13 is connected to the elastic inflatable membrane 12 to inflate and deflate the elastic inflatable membrane 12. The ventilation device... Used to promote gas flow within the tube beam 1; wherein, when the aircraft climbs, the temperature of the energy storage battery pack 11 is higher than the normal operating temperature, the inflation and deflation device 13 deflates the elastic inflatable membrane 12, the exhaust device is turned on, and the energy storage battery pack 11 is cooled down; when the temperature of the energy storage battery pack 11 drops to the normal operating temperature range, the exhaust device is turned off; when the aircraft flies at high altitude, the temperature of the energy storage battery pack 11 is lower than the normal operating temperature, the inflation and deflation device 13 inflates the elastic inflatable membrane 12, the exhaust device is turned off, and the energy storage battery pack 11 is insulated.

[0034] This configuration provides a thermal management system for near-space vehicle tubular beam energy storage batteries. By placing the energy storage battery pack 11 within the tubular beam 1, this system reduces the load on the wing spars while simultaneously using the tubular beam 1 structure to insulate and dissipate heat from the battery pack 11. Rapid heat dissipation and thermal insulation of the battery pack 11 are achieved through the coordinated operation of an elastic inflatable membrane 12 and an exhaust system. This invention features a simple and convenient structural design, good thermal control and reliability, and can meet the heat dissipation and insulation requirements of long-endurance near-space vehicles, while also satisfying the need for lightweight vehicles. Compared with existing technologies, this invention solves the technical problem of insufficient flight performance in near-space vehicles due to efforts to improve the environmental adaptability of energy storage batteries.

[0035] In a specific embodiment of the present invention, the elastic inflatable membrane 12 can be made of high-strength rubber. The high-strength rubber membrane can be inflated and deflated like a balloon. The energy storage battery pack 11 is wrapped in the high-strength rubber membrane and placed inside it. The inflation and deflation of the high-strength rubber membrane can be achieved through the inflation and deflation device 13. After inflation, the gas inside the elastic inflatable membrane 12 essentially stops flowing, and at this time, the gas inside the elastic inflatable membrane 12 plays a role in heat preservation. After deflation, the elastic inflatable membrane 12 is tightly fitted to the outer wall of the energy storage battery pack 11, which is beneficial for heat dissipation of the energy storage battery pack 11. If the exhaust device is turned on at this time, the exhaust device drives the gas flow within the tube beam 1, which can quickly dissipate heat and cool the energy storage battery pack 11.

[0036] Furthermore, in this invention, the configurable inflation / deflation device 13 includes a gas cylinder and a vacuum pump, which are respectively airtightly connected to the elastic inflatable membrane 12. The gas cylinder stores gas to inflate the elastic inflatable membrane 12, and the vacuum pump is used to vent the elastic inflatable membrane 12. As a specific embodiment of this invention, the gas stored in the gas cylinder can be an inert gas. The vacuum pump can be connected to the gas cylinder to refill the extracted inert gas into the gas cylinder, realizing the recycling of the inert gas. The inflation / deflation device 13 can be installed outside the wing spar 1.

[0037] Furthermore, in this invention, in order to improve the heat dissipation performance of the energy storage battery thermal management system, such as... Figure 1 As shown, the configurable exhaust device includes two fans 2, which are located on both sides of the energy storage battery pack 11 along the axial direction of the tube beam 1. One fan is used to draw air into the tube beam 1, and the other fan is used to exhaust air out of the tube beam 1. By setting the intake and exhaust fans on both sides of the energy storage battery pack 11, forced convection can be formed within the tube beam 1, enhancing the heat exchange effect of the energy storage battery pack 11. As a specific embodiment of the present invention, the two fans 2 can be placed at a certain distance from the energy storage battery pack 11. The number of fans can also be increased and the fan models adjusted according to the heat dissipation requirements.

[0038] Furthermore, in this invention, in order to further improve the heat dissipation of the energy storage battery pack 11, such as... Figure 2 and Figure 3 As shown, the configurable energy storage battery pack 11 includes a battery array and an external heat sink 4. The external heat sink 4 is located on a first side and / or a second side of the battery array, with the first side and the second side facing each other. The external heat sink 4 enables effective heat dissipation and temperature equalization of the battery array. As a specific embodiment of the present invention, the external heat sink 4 may be made of aluminum.

[0039] Furthermore, in this invention, in order to maintain the stable installation of the energy storage battery pack 11 in the tube beam 1, and at the same time allow for the expansion of the batteries in the energy storage battery pack 11, such as... Figure 2 and Figure 3 As shown, the configurable energy storage battery pack 11 also includes a foam fixing plate 8, which is located on the third and fourth sides of the battery array. The third and fourth sides are arranged opposite to each other, and the energy storage battery pack 11 is pressed and fixed to the inner wall of the tube beam 1 by the foam fixing plate 8. In this invention, an elastic inflatable membrane 12 wraps the energy storage battery pack 11, and regardless of whether the elastic inflatable membrane 12 is in an inflated or deflated state, the energy storage battery pack 11 is pressed and fixed to the inner wall of the tube beam 1 by the foam fixing plate 8, as shown. Figure 5 As shown. The foam fixing plate 8 has a certain amount of compression, which not only provides cushioned compression and fixation for the energy storage battery pack 11, but also provides a certain space for the expansion of the internal batteries of the energy storage battery pack 11 at high temperatures. As a specific embodiment of the present invention, the foam fixing plate 8 can be made of PMI (polymethacrylimide) foam or shock-absorbing cushioning material. The outer side of the foam fixing plate 8 is designed to conform to the inner wall of the tube beam 1, and the specific dimensions of the foam fixing plate 8 can be designed according to the actual situation.

[0040] Furthermore, in this invention, in order to increase the voltage range of the energy storage battery pack 11 to meet the energy requirements of the aircraft, such as... Figures 2 to 4 As shown, the configurable battery array includes multiple battery packs stacked together. Each battery pack includes a battery cell 6, an internal heat sink 3, and an elastic plate 9. The battery cell 6 is located between the internal heat sink 3 and the elastic plate 9. The internal heat sink 3 is in direct contact with the battery cell 6, which accelerates the dissipation of heat from the battery cell 6. The elastic plate 9 provides space for the battery cell 6 to expand.

[0041] In a specific embodiment of the present invention, the internal heat dissipation plate 3 can be made of aluminum plate, and the elastic plate 9 can be made of foam material. The specific dimensions of the elastic plate 9 can be designed according to actual conditions. The number of battery packs can be set according to actual flight needs, such as... Figure 4 As shown, the battery array may include 12 battery packs with a voltage range of 3-4.2V. The tabs 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.

[0042] Furthermore, in this invention, to further accelerate the heat dissipation from the battery cell 6, an internal heat sink 3 can be provided with a cavity, with the battery cell 6 located within the cavity of the internal heat sink 3, and multiple internal heat sinks 3 in contact with an external heat sink 4. By providing multiple internal heat sinks 3 in contact with the external heat sink 4, on the one hand, the heat inside the battery cell 6 can be sequentially transferred to the outside of the energy storage battery pack 11 through the internal heat sink 3 and the external heat sink 4, accelerating the heat dissipation and cooling of the energy storage battery pack 11; on the other hand, it can balance the temperature difference between multiple battery cells, avoiding excessively high or low temperatures in a single battery, thereby improving the output performance of the energy storage battery. As a specific embodiment of this invention, such as... Figure 4 As shown, the cross-section of the internal heat sink 3 is shaped like an arrow, and the battery cell 6 is located inside the recess. Multiple surfaces of the battery cell 6 can be arranged to contact the internal heat sink 3 to improve heat dissipation efficiency.

[0043] Furthermore, in this invention, in order to obtain the accurate temperature of the battery cell 6, such as... Figure 4 As shown, any configurable battery pack also includes a temperature sensor 10, which is located between the battery cell 6 and the elastic plate 9. The temperature sensor 10 can monitor the surface temperature of each battery cell 6 in real time, thereby enabling timely heat dissipation or insulation of the energy storage battery pack 11.

[0044] Furthermore, in this invention, in order to reduce the weight of the energy storage battery pack 11, such as... Figure 2 and Figure 3 As shown, the configurable energy storage battery pack 11 also includes a fixing strap 7, which surrounds the battery array and the foam fixing plate 8. The fixing strap 7 secures multiple battery packs in the battery array and the foam fixing plate 8, avoiding the use of a housing and support structure. This meets the requirements for lightweighting and simplification, facilitates wing load reduction, improves the energy-to-weight ratio of the energy storage battery pack 11, and thus reduces the overall weight of the aircraft. In a specific embodiment of the invention, the fixing strap 7 can be made of polyimide tape.

[0045] Furthermore, in this invention, in order to achieve monitoring of battery voltage, current, and temperature, such as... Figure 2 and Figure 3As shown, the configurable energy storage battery pack 11 also includes a BMS5 (Battery Management System), located on the fifth side of the battery array. The BMS5 is connected to the battery array, the charging / draining device 13, and the ventilation device. The BMS5 enables real-time monitoring and control of the battery array, the charging / draining device 13, and the ventilation device, allowing for timely temperature adjustments to the energy storage battery pack 11. In a specific embodiment of the invention, the BMS5 is connected to multiple battery cells 6, multiple temperature sensors 10, gas cylinders and a vacuum pump, and two fans 2 within the battery array. The BMS5 can control the gas cylinders, the vacuum pump, and the two fans 2 based on the real-time temperature of the battery cells 6 measured by the temperature sensors 10, effectively dissipating heat or maintaining the temperature of the multiple battery cells 6.

[0046] Using the above configuration, during the aircraft's climb, the energy storage battery pack 11 discharges at a high power, generating significant heat. When the temperature sensor 10 detects that the temperature of the individual battery cell 6 is higher than the normal operating temperature, the BMS5 controls the air extraction device to vent the elastic inflatable membrane 12. After venting, the elastic inflatable membrane 12 adheres tightly to the outer wall of the energy storage battery pack 11. Simultaneously, the BMS5 controls the two fans 2 to automatically turn on, creating forced convection within the circular tube beam 1. Air flows into the tube beam 1 through one fan 2, passes through the elastic inflatable membrane 12, flows over the two external heat dissipation aluminum plates on the side of the energy storage battery pack 11, and exits through the other fan 2. At this time, the air acts as a heat exchange medium. When the temperature sensor 10 detects that the temperature of the individual battery cell 6 is within the normal operating temperature range, the BMS5 controls the fan 2 to turn off. At this time, the air inside the circular tube beam 1 is essentially still, and the air provides insulation. When the aircraft is flying at high altitude, the lowest outside temperature can reach -55℃. At this time, the energy storage battery pack 11 is in a high-altitude low-temperature environment. The temperature sensor 10 collects the temperature of the battery cell 6, which is lower than the normal operating temperature. The BMS5 controls the gas cylinder to inflate the elastic inflatable membrane 12. After the inflatable membrane 12 is inflated, the gas inside the elastic inflatable membrane 12 no longer flows, and the internal gas plays a heat preservation role, ensuring that the temperature of the energy storage battery is at the normal operating temperature.

[0047] The thermal management system for energy storage batteries in the tube beam of this invention is simple and convenient to design, has good thermal control and reliability, meets the heat dissipation and insulation requirements of long-endurance near-space vehicles, and does not require uniform environmental control for the entire vehicle. This invention can rationally utilize the structure to reduce the overall weight of the aircraft. By utilizing the rational layout of the energy storage battery pack 11 within the tube beam 1, it can reduce the load on the wings, further reducing the proportion of structural weight.

[0048] To gain a further understanding of the present invention, the following description is provided in conjunction with... Figures 1 to 5 The thermal management system for near-space vehicle tubular beam energy storage battery of the present invention will be described in detail.

[0049] like Figures 1 to 5 As shown in the figure, a thermal management system for a near-space vehicle wing spar energy storage battery is provided according to a specific embodiment of the present invention. The thermal management system includes: 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 within the wing spar 1 of the near-space vehicle. The energy storage battery pack 11 is located within the elastic inflatable membrane 12. The gas cylinder stores gas to inflate the elastic inflatable membrane 12. The air extraction device is used to exhaust gas from the elastic inflatable membrane 12. The two fans 2 are located on both sides of the energy storage battery pack 11 along the axial direction of the spar 1; one fan is used to draw air into the spar 1, and the other fan is used to exhaust air from the spar 1.

[0050] The energy storage battery pack 11 includes: a battery array, an external heat sink 4, a foam fixing plate 8, a fixing strap 7, and a battery management system (BMS) 5. The external heat sink 4 is located on the first and / or second side of the battery array, and the foam fixing plate 8 is located on the third and fourth sides of the battery array. The energy storage battery pack 11 is fixed to the inner wall of the tube beam 1 by compression through the foam fixing plate 8. The fixing strap 7 is arranged around the battery array and the foam fixing plate 8. The BMS 5 is located on the fifth side of the battery array and is connected to the battery array, the charging and decharging device 13, and the ventilation device.

[0051] The battery array includes multiple battery packs stacked together. Each battery pack includes a battery cell 6, an internal heat sink 3, a temperature sensor 10, and an elastic plate 9. The battery cell 6 is located between the internal heat sink 3 and the elastic plate 9, and the temperature sensor 10 is located between the battery cell 6 and the elastic plate 9.

[0052] In summary, this invention provides a thermal management system for a near-space vehicle's tubular beam energy storage battery. This system, by housing the energy storage battery pack within the tubular beam, reduces the load on the wing spars while simultaneously utilizing the beam structure for insulation and heat dissipation. Rapid heat dissipation and thermal insulation of the battery pack are achieved through the coordinated operation of an elastic inflatable membrane and an exhaust system. This invention features a simple and convenient structural design, good thermal control and reliability, and can meet the heat dissipation and insulation requirements of long-endurance near-space vehicles, while also satisfying the need for lightweight design. Compared with existing technologies, this invention solves the technical problem of insufficient flight performance in near-space vehicles due to efforts to improve the environmental adaptability of energy storage batteries.

[0053] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0054] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0055] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A thermal management system for a near-space vehicle's tubular beam energy storage battery, characterized in that, The thermal management system for the energy storage battery of the near-space vehicle wing spar includes: an elastic inflatable membrane (12), an inflation / deflation device (13), an energy storage battery pack (11), and an exhaust device. The elastic inflatable membrane (12), the energy storage battery pack (11), and the exhaust device are located within the wing spar (1) of the near-space vehicle. The energy storage battery pack (11) is located within the elastic inflatable membrane (12). The inflation / deflation device (13) is connected to the elastic inflatable membrane (12) to inflate and deflate the elastic inflatable membrane (12). The exhaust device is used to promote gas flow within the spar (1). When the aircraft climbs, the temperature of the energy storage battery pack (11) is higher than the normal operating temperature. The inflation and deflation device (13) vents the elastic inflatable membrane (12), and the ventilation device is turned on to cool down the energy storage battery pack (11). When the temperature of the energy storage battery pack (11) drops to the normal operating temperature range, the ventilation device is turned off. When the aircraft flies at high altitude, the temperature of the energy storage battery pack (11) is lower than the normal operating temperature. The inflation and deflation device (13) inflates the elastic inflatable membrane (12), and the ventilation device is turned off to insulate the energy storage battery pack (11).

2. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 1, characterized in that, The elastic inflatable membrane (12) is made of high-strength rubber.

3. The thermal management system for near-space vehicle tubular beam energy storage batteries according to claim 1, characterized in that, The inflation / deflation device (13) includes a gas cylinder and a pumping device. The gas cylinder and the pumping device are respectively airtightly connected to the elastic inflatable membrane (12). The gas cylinder stores gas to inflate the elastic inflatable membrane (12), and the pumping device is used to deflate the elastic inflatable membrane (12).

4. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 3, characterized in that, The gas stored in the gas cylinder is an inert gas.

5. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 1, characterized in that, The exhaust device includes two fans (2), which are located on both sides of the energy storage battery pack (11) along the axial direction of the tube beam (1). One fan is used to draw air into the tube beam (1), and the other fan is used to exhaust air out of the tube beam (1).

6. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 1, characterized in that, The energy storage battery pack (11) includes a battery array and an external heat sink (4), wherein the external heat sink (4) is located on a first side and / or a second side of the battery array, and the first side and the second side are arranged opposite to each other.

7. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 6, characterized in that, The energy storage battery pack (11) also includes a foam fixing plate (8), which is located on the third and fourth sides of the battery array. The third and fourth sides are arranged opposite to each other. The energy storage battery pack (11) is fixed to the inner wall of the tube beam (1) by the foam fixing plate (8).

8. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 7, characterized in that, The foam fixing board (8) is made of PMI foam.

9. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 6, characterized in that, The battery array includes multiple battery packs stacked together. Each battery pack includes a battery cell (6), an internal heat sink (3), and an elastic plate (9). The battery cell (6) is located between the internal heat sink (3) and the elastic plate (9).

10. The thermal management system for a near-space vehicle tubular beam energy storage battery according to claim 9, characterized in that, The elastic plate (9) is made of foam material.

11. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 9, characterized in that, The internal heat sink (3) has a cavity, the battery cell (6) is located in the cavity of the internal heat sink (3), and multiple internal heat sinks (3) are in contact with the external heat sink (4).

12. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 9, characterized in that, The external heat sink (4) and the internal heat sink (3) are made of aluminum plates.

13. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 9, characterized in that, Each battery pack also includes a temperature sensor (10) located between the battery cell (6) and the elastic plate (9).

14. The thermal management system for near-space vehicle tubular beam energy storage battery according to claim 7, characterized in that, The energy storage battery pack (11) also includes a fixing strap (7) which is arranged around the battery array and the foam fixing plate (8).

15. The thermal management system for a near-space vehicle tubular beam energy storage battery according to any one of claims 6 to 14, characterized in that, The energy storage battery pack (11) also includes a BMS (5), which is located on the fifth side of the battery array. The BMS (5) is connected to the battery array, the charging and discharging device (13), and the exhaust device.

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