An incoming flow pneumatic self-cooling aircraft relates to the field of aircraft thermal protection design, the aircraft is of a multi-layer structure, two layers of the aircraft from outside to inside are a first structure layer and a second structure layer, a plurality of through holes are machined in the first structure layer, so that a plurality of Laval nozzles are formed in the first structure layer, and the second structure layer is formed in the second structure layer. A cavity is formed between the first structure layer and the second structure layer and communicates with a jet flow opening in the tail of the aircraft, one end of the through hole communicates with the cavity, and the other end of the through hole communicates with a flow field on the outer surface of the first structure layer. A miniature reverse spray pipe array is established on a surface matrix structure of an aircraft, gas expansion is realized through a heat insulation throttling effect when pneumatic energy in gas flowing around the aircraft passes through a spray pipe, periodic locking of gas flowing expansion and compression is relieved through a heat insulation throttling spray pipe, a pneumatic heating effect is converted into pneumatic refrigeration, and the air cooling effect is improved. The purposes of temperature reduction and thermal protection of the aircraft are achieved.
一种来流气动自冷却飞行器,涉及飞行器热防护设计领域,所述飞行器为多层结构,飞行器的从外向内的两层为第一结构层和第二结构层,第一结构层加工有多个通孔,以在第一结构层形成多个拉瓦尔喷管,第一结构层和第二结构层之间设置有空腔,空腔与飞行器的尾部的喷流口连通,通孔的一端与空腔连通,通孔的另一端与第一结构层外表面的流场连通。在飞行器表面基体结构上建立微型的反向喷管阵列,通过飞行器周围气体流动中的气动能量通过喷管时的绝热节流效应,通过绝热节流喷管,实现气体的膨胀,解除气体流动膨胀、压缩的周期锁定,将气动加热效应转化为气动制冷,实现温度降低,达到飞行器热防护的目的。
Incoming flow pneumatic self-cooling aircraft
一种来流气动自冷却飞行器
2024-01-26
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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