Battery temperature control system and method for high-altitude electrically-driven aircraft
Battery temperature control system and method for high-altitude electrically-driven aircraft
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.
本发明提供一种高空电驱动飞机电池温度控制系统和方法，该系统位于飞机前设备舱内，包括进气道、温度传感器和空气控制阀门；进气道由自然风进气道、动力电机热源进气道和温度调节进气道构成；空气控制阀门位于自然风进气道和动力电机热源进气道与温度调节进气道之间；温度传感器采集电池的实时温度，将温度信号传至所述空气控制阀门；空气控制阀门根据电池系统温度，通过控制阀门开合，控制自然风和动力电机热源空气的流量。本发明克服现有系统中高低空飞行工况散热和加温功能不兼顾的不足，并节省飞机电池电能，延长续航时间。
Document information
Battery temperature control system and method for high-altitude electrically-driven aircraft
一种高空电驱动飞机电池温度控制系统和方法
2021-03-19
Patent
Electronic Resource
Chinese