The invention provides a high-altitude aircraft electric propulsion system which comprises a driving device support, wherein the support comprises a plurality of heat pipes, each heat pipe is providedwith a cavity, liquid capable of being evaporated and absorbing heat is arranged in each cavity, and the heat pipes are connected with a driving device in a heat transfer mode. The high-altitude aircraft electric propulsion system is provided with the heat pipes, a cavity is formed in each heat pipe, liquid is arranged in each cavity, and each heat pipe is in heat transfer connection with the driving device and used for absorbing heat generated by the operation of the driving device, so that heat dissipation of the driving device is achieved. The steam in the heat pipes is subjected to heat dissipation and cooling through cooling fins arranged on the heat pipes in a sleeving manner. Meanwhile, the heat pipes are obliquely arranged, so that the liquid flows back to the heating part of thedriving device under the action of the gravity of the liquid, or the filler is arranged in the cavity of each heat pipe, and the liquid is transferred to the lower end of each heat pipe by utilizing capillarity generated between the filler and the liquid.
本发明提供一种高空飞行器电推进系统,包括:驱动装置支架,支架包括有多根热管,每一根热管具有空腔,于空腔内设置有可蒸发吸热的液体,热管与驱动装置热传递连接。本发明公开了一种高空飞行器电推进系统,该高空飞行器电推进系统通过设置热管,在热管内设置空腔,在空腔内设置液体,热管与驱动装置热传递连接、用于吸收驱动装置运行所产生的热量,从而实现对驱动装置的散热。再通过套设于热管上的散热片对热管内的蒸汽进行散热冷却。同时采用将热管倾斜设置方式使液体在自身重力作用下回流至驱动装置的发热部位,或者通过在热管的空腔内设置填充物,利用填充物和液体之间产生的毛细现象将液体传递到热管的下端。
High-altitude aircraft electric propulsion system
一种高空飞行器电推进系统
2020-05-08
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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