The invention relates to the technical field of aviation, and particularly discloses an air rudder active cooling system of a hypersonic aircraft, which comprises a leading edge skin and a trailing edge skin, a rudder shaft connected with the leading edge skin and the trailing edge skin is arranged between the leading edge skin and the trailing edge skin, at least two leading edge skin channels are arranged in the leading edge skin, and the leading edge skin channels are communicated with the leading edge skin. All the leading edge skin channels are communicated in the leading edge area; at least two trailing edge skin channels are arranged in the trailing edge skin, and all the trailing edge skin channels are communicated in a trailing edge area; the rudder shaft comprises a working medium input channel and a working medium output channel, the working medium input channel is communicated with at least one front edge skin channel, the working medium output channel is communicated with at least one rear edge skin channel, and the front edge skin channel which is not communicated with the working medium input channel is communicated with the rear edge skin channel which is not communicated with the working medium output channel. And the air rudder can be cooled through an active thermal protection technology.
本发明涉及航空技术领域,并具体公开了一种高超声速飞行器的空气舵主动冷却系统,包括前缘蒙皮以及后缘蒙皮,在前缘蒙皮与后缘蒙皮之间设置有与二者连接的舵轴,所述前缘蒙皮中设置有至少两个前缘蒙皮通道,所有前缘蒙皮通道在前缘区域连通;所述后缘蒙皮中设置有至少两个后缘蒙皮通道,所有后缘蒙皮通道在后缘区域连通;所述舵轴包括工质输入通道和工质输出通道,所述工质输入通道与至少一个前缘蒙皮通道连通,所述工质输出通道与至少一个后缘蒙皮通道连通,未与工质输入通道连通的前缘蒙皮通道和未与工质输出通道连通的后缘蒙皮通道连通。可通过主动热防护技术对空气舵进行冷却。
Aerial rudder active cooling system of hypersonic aircraft
一种高超声速飞行器的空气舵主动冷却系统
2025-01-10
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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