The invention provides a thermal protection device for the leading edge of a rudder (wing) of a hypersonic aircraft, belongs to the field of aerospace hypersonic aircrafts, and relates to a quartz/phenolic aldehyde composite material process and a carbon/phenolic aldehyde composite material process. Comprising a high-temperature-resistant carbon/ceramic front edge, a carbon/phenolic aldehyde connecting piece, a quartz/phenolic aldehyde heat-proof layer and a metal bearing structure. The high-temperature-resistant rudder (wing) front edge (1), the carbon/phenolic aldehyde high-temperature-resistant heat-insulation connecting piece (2), the quartz/phenolic aldehyde rudder (wing) surface heat-proof layer (3) and the rudder (wing) metal bearing structure (4) are arranged from top to bottom. Wherein the carbon/phenolic aldehyde high-temperature-resistant heat-insulating connecting piece (2) and the quartz/phenolic aldehyde rudder (wing) surface heat-proof layer (3) are connected together in a weaving manner when the prefabricated body is woven, so that the integrity of the structure is enhanced. The invention provides a low-cost hypersonic aircraft rudder (wing) front edge heat-proof device in a mode of combining a high-temperature-resistant front edge with an ablation rudder (wing) surface heat-proof layer, and the temperature-resistant grade of the front edge can be 2500 DEG C or above.
本发明提供了一种高超音速飞行器舵(翼)前缘防热装置,属于航空航天高超声速飞行器领域,涉及石英/酚醛复合材料工艺、碳/酚醛复合材料工艺。包括:耐高温碳/陶瓷前缘、碳/酚醛连接件、石英/酚醛防热层以及金属承载结构。从上至下为耐高温舵(翼)前缘[1]、碳/酚醛耐高温隔热连接件[2]、石英/酚醛舵(翼)面防热层[3]、舵(翼)金属承载结构[4]。其中碳/酚醛耐高温隔热连接件[2]与石英/酚醛舵(翼)面防热层[3]结构在预制体编织时通过编织方式连接在一起,增强结构的整体性。本发明以耐高温前缘与烧蚀舵(翼)面防热层相结合的方式,提供了一种低成本高超音速飞行器舵(翼)前缘防热装置,可以使前缘耐温等级在2500℃以上。
Heatproof device for leading edge of rudder (wing) of hypersonic aircraft
一种高超音速飞行器舵(翼)前缘防热装置
2024-12-31
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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