Battery temperature control system and method for high-altitude electrically-driven aircraft

Abstract

The invention provides a battery temperature control system and method for a high-altitude electrically-driven aircraft. The battery temperature control system is located in a front equipment cabin ofthe aircraft, and comprises an air inlet channel, a temperature sensor and air control valves, wherein the air inlet channel is composed of a natural air inlet channel body, a power motor heat sourceair inlet channel body and a temperature adjusting air inlet channel body; the air control valves are located among the natural air inlet channel and the power motor heat source air inlet channel andthe temperature adjusting air inlet channel. the temperature sensor collects the real-time temperature of a battery and transmits a temperature signal to the air control valves; and the air control valves control the flow of natural wind and heat source air of a power motor by controlling opening and closing of the valves according to the temperature of a battery system. The defect that in an existing system, the heat dissipation function and the heating function are not considered at the same time under a high-low-altitude flight working condition is overcome, the electric energy of the battery of the aircraft is saved, and endurance time is prolonged.

Description

technical field [0001] The invention relates to the technical field of electric-driven aircraft, in particular to a battery temperature control system and method for high-altitude electric-driven aircraft. Background technique [0002] The technical difficulty of the high-altitude electric drive aircraft battery temperature control system lies in how to take into account the high-altitude and low-altitude flight conditions, that is, the same system has two functions of heat dissipation and heating, and does not consume or consume less energy storage of the aircraft. The living environment of high-altitude electric-driven aircraft is harsh, especially the high-altitude ambient temperature is low, and the battery system of electric-driven aircraft needs certain heating measures. Existing technologies mostly use passive insulation methods, such as outsourcing batteries with insulation materials, but this method does not take into account the low-altitude flight conditions. At t...

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Problems solved by technology

[0003] The purpose of the present invention is to overcome the deficiencies of the prior art, and provide a battery temperature control system and method for high-altitude electric-driven aircraft, which can solve the problems of high-altitude and low-altitude flight conditions that do not take into account the heat dissipation and heating functions and the waste of electric energy in the existing system

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