The invention relates to a high-speed aircraft thermal management system design method based on an aerodynamic heat utilization technology, a high-speed aircraft thermal management system is designed through the method, and the system comprises a thermal control box arranged in a control surface, a cooling channel arranged at the bottom end of the control surface and a cooling assembly arranged in a fuselage; a gap is formed between the bottom end of the control surface and the machine body; an exhaust port is formed in the cooling channel towards the gap; one end of the cooling assembly is communicated with the thermal control box through a pipeline, a pressure control piece is arranged on the pipeline, and the other end is communicated with the cooling channel; and a cooling working medium is arranged in the thermal control box and absorbs heat of the control surface to generate phase change. Heat is absorbed through the thermal control box and the cooling assembly, the cooling working medium after phase change is discharged from the exhaust port, multiple effects of front edge resistance reduction and heat protection and semi-active thermal control of gaps, connecting pieces and other parts can be achieved, and the safe and stable working temperature of the servo mechanism is effectively guaranteed.
本申请涉及一种基于气动热利用技术的高速飞行器热管理系统设计方法,通过所述方法设计高速飞行器热管理系统,系统包括:设置在控制面内的热控箱,设置在控制面底端的冷却通道,以及设置在机身内的冷却组件;控制面底端与机身之间具有间隙,冷却通道朝向间隙处开设有排气口;冷却组件的一端通过管道与热控箱连通,管道上设置有压力控制件,另一端与冷却通道连通;热控箱内具有冷却工质,冷却工质吸收控制面的热量产生相变。本申请通过热控箱与冷却组件吸热,并将相变后的冷却工质从排气口排出,能够实现前缘减阻防热,间隙、连接件等部位半主动热控的多重功效,有效保证了伺服机构安全、稳定的工作温度。
High-speed aircraft thermal management system design method based on aerodynamic heat utilization technology
一种基于气动热利用技术的高速飞行器热管理系统设计方法
2024-05-07
Patent
Electronic Resource
Chinese
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