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CN-122025967-A - Battery compartment and electric aircraft

CN122025967ACN 122025967 ACN122025967 ACN 122025967ACN-122025967-A

Abstract

The application discloses a battery compartment and an electric aircraft. The battery compartment comprises a compartment body, a cover plate and a battery. The cover plate and the bin body are enclosed to form a containing space, and the battery is contained in the containing space. The cover plate comprises a frame and a blade, wherein the frame is provided with an opening, the opening is communicated with the accommodating space, the blade is connected with the frame, at least part of the blade is made of shape memory alloy, the shape memory alloy generates reversible phase change along with temperature change, and the blade is used for opening or closing the opening. Therefore, the opening degree adjustment of the blade without external energy driving is realized based on the reversible phase change of the shape memory alloy, so that the heat dissipation capacity is matched with the heat load of the battery in real time, meanwhile, the weight and the structural strength are both considered, the airborne electric energy is not required to be consumed, and the endurance time of the aircraft is prolonged.

Inventors

  • HUANG HE
  • LIU XINYING
  • LI DAN
  • GAO YIFEI
  • ZHANG JINGQI
  • CHEN YING

Assignees

  • 一汽旗翼(深圳)科技有限公司

Dates

Publication Date
20260512
Application Date
20251230

Claims (10)

  1. 1. A battery compartment, comprising: A bin body; the cover plate and the bin body are enclosed to form a containing space; the battery is accommodated in the accommodating space; The cover plate comprises a frame and a blade, wherein the frame is provided with an opening, the opening is communicated with the accommodating space, the blade is connected with the frame, at least part of the blade is made of shape memory alloy, the shape memory alloy generates reversible phase change along with temperature change, and the blade is used for opening or closing the opening.
  2. 2. The battery compartment of claim 1, wherein the blade includes a blade body and a connecting portion, one end of the connecting portion being connected to the frame, the other end of the connecting portion being connected to the blade body, at least one of the blade body and the connecting portion being made of the shape memory alloy.
  3. 3. The battery compartment of claim 2, wherein the connection portion is disposed at a side of the frame facing the receiving space.
  4. 4. The battery compartment of claim 2, wherein the number of the connection portions is plural, and the plural connection portions are disposed at equal intervals along the length direction of the blade.
  5. 5. The battery compartment of claim 2, wherein the blade body has a thickness of 0.8mm to 1.2mm.
  6. 6. The battery compartment of claim 2, wherein the connecting portion has a thickness of 0.8mm to 1.2mm and a width of 8mm to 12mm.
  7. 7. The battery compartment of any of claims 1-6, wherein the shape memory alloy is a nickel-titanium-based shape memory alloy having an austenite finish temperature that is less than a maximum operating temperature of the battery compartment.
  8. 8. The battery compartment of any of claims 1-6, wherein the frame comprises a plurality of the openings, the plurality of openings being equally spaced along a length of the frame, the number of blades being a plurality, the blades being disposed in one-to-one correspondence with the openings.
  9. 9. The battery compartment of any of claims 1-6, wherein the surface of the blade is provided with a heat radiation coating.
  10. 10. An electric aircraft comprising an aircraft body and a battery compartment according to any one of claims 1 to 9, the battery compartment being electrically connected to the aircraft body, the battery compartment being for powering the aircraft body.

Description

Battery compartment and electric aircraft Technical Field The application belongs to the technical field of electric vertical take-off and landing aircraft thermal management, and particularly relates to a battery compartment and an electric aircraft. Background Following electric vertical take-off and landing aircraft (ELECTRIC VERTICAL TAKE)Off AND LANDING, EVTOL) and the rapid development of long-endurance electric fixed-wing aircrafts, a great amount of joule heat generated by a high-energy-density power battery in the high-rate charge and discharge process has become a key bottleneck for restricting flight safety and endurance performance. The heat dissipation systems such as the electric fan, the liquid cooling plate or the thermoelectric refrigerating system have the problems of high energy consumption, complex structure, heavy weight, high maintenance cost and the like, and limit the effective load and the flight efficiency of the aircraft. The fixed shutter or the fusing type heat dissipation opening cover has the problem of unstable heat dissipation performance, excessive heat dissipation at low temperature and insufficient heat dissipation at high temperature, and seriously influences the flight task adaptability. In addition, in long-term operation, because the battery compartment structure produces micron-sized displacement because of expend with heat and contract with cold and vibration fatigue, the seal structure of battery compartment easily takes place permanent deformation, causes sealed inefficacy, steam invasion and potential thermal runaway risk. Disclosure of Invention The application aims to at least solve the technical problems that the battery compartment of the electric aircraft is slow in heat radiation response, insufficient in heat radiation performance and unsatisfactory in lightweight design of the electric aircraft to a certain extent. Therefore, the battery compartment and the electric aircraft provided by the application have the advantages that the battery compartment does not need external energy, can be adaptively adjusted along with temperature, and can maintain reliable sealing performance in the whole life cycle, so that the severe requirements of the electric aircraft on light weight, high reliability and seaworthiness safety are met. In a first aspect, the battery compartment provided by the embodiment of the application comprises a compartment body, a cover plate and a battery, wherein the cover plate and the compartment body are enclosed to form a containing space, the battery is contained in the containing space, the cover plate comprises a frame and a blade, the frame is provided with an opening, the opening is communicated with the containing space, the blade is connected with the frame, at least part of the blade is made of a shape memory alloy, the shape memory alloy generates reversible phase change along with temperature change, and the blade is used for opening or closing the opening. Therefore, the blade realizes the opening adjustment without external energy driving based on the reversible phase transformation of the shape memory alloy (Shape Memory Alloys, SMA), and solves the defects of high wind resistance and insufficient heat dissipation under high load of the traditional passive heat dissipation. Due to the phase change continuity of the SMA, the blades can stay at different positions between the opening and the closing opening along with temperature change, so that the heat dissipation capacity is matched with the heat load of the battery in real time, and the risk of reduced battery activity caused by excessive heat dissipation at low temperature or thermal runaway caused by insufficient heat dissipation at high temperature is avoided. At least part of the blades are made of SMA, the weight and the structural strength of the SMA are both considered, and the SMA does not need complex driving components such as a motor, a pump valve and the like, so that the weight of the intelligent air-conditioning system is reduced compared with that of a traditional active heat-dissipating system, and meanwhile, the problem that the energy consumption of the active heat-dissipating system occupies battery output is solved, and the endurance time of an aircraft is indirectly prolonged. The SMA material has excellent fatigue resistance, phase change drift of less than 0.5 degrees after thousands times of thermal cycles, service life of more than 10000 hours, and the sealing structure design of the cover plate and the bin body can effectively prevent water vapor invasion, and meanwhile, the problem of sealing failure caused by vibration fatigue of the traditional mechanical heat dissipation cover is avoided by SMA driving. In some possible embodiments, the blade comprises a blade body and a connecting part, one end of the connecting part is connected with the frame, the other end of the connecting part is connected with the blade body, and the blade body and the c