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为了评估固冲发动机硅基绝热层的烧蚀性能,对硅基绝热层的烧蚀形成机制进行了分析并建立了数值模型。硅基绝热层烧蚀由气动冲蚀,化学烧蚀,颗粒剥蚀三个部分构成。数值结果表明,硅基绝热层失效的主要原因是气动冲蚀,化学烧蚀与颗粒剥蚀影响较小。理论计算同试验获得的烧蚀形态基本吻合,冲压发动机严重烧蚀部位在进气道两侧的下游区域。从结构设计上看,冲压发动机防隔热设计的重点应是降低冲压发动机气流冲蚀影响。
In order to evaluate the ablation performance of the solid insulation engineered silicon-based insulation layer, the ablation mechanism of the silicon-based insulation layer was analyzed and a numerical model was established. Silicon-based insulation ablation by pneumatic erosion, chemical ablation, particle erosion composed of three parts. Numerical results show that the main reason for the failure of silicon-based thermal insulation layer is pneumatic erosion, which has little effect on chemical ablation and grain erosion. The theoretical calculation is in good agreement with the ablation morphology obtained from the test, and the severe ablation site of the ramjet engine is in the downstream area on both sides of the inlet. From the structural design point of view, stamping engine anti-thermal insulation design should focus on reducing the impact of ramjet air erosion.