用于自适应进气道的扁薄球壳双稳态特性分析  

ANALYSIS OF BI-STABLE BEHAVIOR OF SHALLOW THIN SPHERICAL SHELL APPLIED IN ADAPTIVE INLET

作　　者：张平[1] 周丽[1] 邱涛[2] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [2]沈阳飞机设计研究所,沈阳110035

出　　处：《工程力学》2013年第10期264-271,共8页Engineering Mechanics

基　　金：国家自然科学基金项目(11172128;61161120323);江苏省"六大人才高峰"项目(2010-JZ-004);江苏省普通高校研究生科研创新计划项目(CXZZ12_0139);高等学校博士学科点专项科研基金项目(20123218110001);江苏高校优势学科建设工程项目

摘　　要：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 can adjust the capture area and throat area of an inlet by actively controlling the structural shape of the lip and internal wall, so as to enhance the inlet performances of fighters in a large speed domain. A bump inlet is a kind of advanced inlet, but its performance of off-design points is limited due to its unchangeable bump surface shape. Aiming at the problem, this article presents an idea of using a bi-stable configuration of the shallow thin spherical shell to adjust the shape of the bump surface to improve the inlet performance at different speeds. For the hinge supported shallow thin spherical shell, the existence condition of a bi-stable configuration is analyzed, and the effects of loading mode and position on the bi-stable behavior of the shell are studied, also the relations between shell parameters and driving loads, loading stroke and internal stress are developed at the stable configuration transition moment, to provide a design reference for the shape control of the bi-stable configuration of the shallow thin spherical shell and its application in an adaptive inlet.

关 键 词：主动变形 自适应鼓包 进气道 扁薄球壳 双稳态构型 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程]