The thermal protection structure comprises a first porous medium layer arranged on the arc-shaped wall face of the front edge of the aircraft and a plurality of second porous medium layers arranged on the upper wall face and the lower wall face of the front edge of the aircraft at intervals in the flow direction. Solid walls are arranged between the first porous medium layers and the second porous medium layers and between every two adjacent second porous medium layers; the porosity of each second porous medium layer is firstly increased and then reduced along the flow direction, and the porosity of the first porous medium layer is smaller than that of the second porous medium layer at the most upstream. The method is applied to the field of thermal protection of aircrafts, the problem of local overheating existing in a traditional sweating cooling technology is effectively solved through the synergistic effect of the intermittent sweating layout and the gradient porosity material, and the situation that the cooling efficiency is reduced due to overheating of a cooling agent is avoided.
本发明公开了一种飞行器前缘热防护结构,包括设在飞行器前缘弧形壁面处的第一多孔介质层,以及多个沿流向间隔设在所述飞行器前缘上、下壁面处的第二多孔介质层;所述第一多孔介质层与所述第二多孔介质层之间、相邻两所述第二多孔介质层之间均设有固体壁;各所述第二多孔介质层的孔隙率沿流向先增大、后减小,所述第一多孔介质层的孔隙率小于最上游所述第二多孔介质层的孔隙率。本发明应用于飞行器热防护领域,通过间断发汗布局和梯度孔隙率材料的协同作用,有效解决了传统发汗冷却技术中存在的局部过热问题,避免了因冷却剂过热而导致的冷却效率下降。
Aircraft leading edge thermal protection structure
一种飞行器前缘热防护结构
06.05.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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