摘要
本文介绍了笔者在静气动弹性效应的理论与实验研究中的若干进展。静气动弹性研究涉及作用于飞行器的气动力与结构变形的相互作用,是研究飞行器的风洞试验数据和飞行试验数据相关性的一个重要方面。文中讨论了在进行静气动弹性分析时对一些问题的处理,并对风洞试验模型及某型导弹进行了计算,结果表明:对于所选算例,结构变形使升力线斜率降低,压心前移。
In this paper, some evolution of theoretical and test research in static aeroelastic effect are presented. The research of static aero-elastic effect involves the interaction between the aerodynamic force acting on the flying vehicle and its structural deformation. It is a importance aspect of research on the relativity between the testing data in wind tunnel and in flight of the flying vehicle. In this paper, the processing methods for some problems in analysis of static aeroelasticity are discussed and a test model in wind tunnel and a guided missile in flight are calculated. The result shows that the deformation of the structures will decrease the slope of lifting line and make the center of pressure moves a-head.
出处
《上海力学》
CSCD
1999年第3期216-222,共7页
Chinese Quarterly Mechanics
