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自适应进气道通过主动控制唇口和内管道的结构形状,能够调节进气道的捕获面积和喉道面积,从而提升战斗机在宽速域内的进气道性能。鼓包进气道是一种先进的进气道,但是鼓包面形状不可调节,限制了其在非设计点的性能。该文针对该问题,提出利用扁薄球壳的双稳态构型调节鼓包面形状,从而改善进气道在不同速度下的使用性能。研究了铰支边界的圆底扁薄球壳存在双稳态构型需要的条件,分析了加载方式和加载位置对壳体双稳态特性的影响,并给出稳态构型转换时壳体结构参数与驱动载荷、加载行程以及结构内应力的关系,为扁薄球壳双稳态构型的形状控制以及在自适应进气道上的应用提供设计参考。
Adaptive Inlet The intake port capture area and throat area can be adjusted by actively controlling the configuration of the lip and the inner pipe to enhance the performance of the fighter’s inlet over a wide range of speeds. The drum inlet is an advanced air intake, but its shape can not be adjusted, limiting its performance at non-design points. In view of this problem, this paper proposes the use of the bistable configuration of a thin spherical shell to adjust the shape of the drum envelope to improve the performance of the intake port at different speeds. The conditions for the existence of a bistable configuration of the round and flat spherical shell with hinged support are studied. The influence of the loading method and loading position on the bistable characteristics of the shell is analyzed. The relationship between the structural parameters and the driving load, the loading stroke and the internal stress of the structure provides the design reference for the shape control of the bimodal spherical shell with bistable configuration and the application in the adaptive inlet.