摘要
本文把文献[1]中的无控弹体气动弹性发散分析方法推广成有控弹体气动伺服弹性发散分析方法。文献[1]的方法毋需结构固有振型为原始数据,且数学工具简单。经本文推广后的方法保持了原法的优点。
The analysis method of aeroelastic divergence for a fuselage without control system in refer- ence [1] is generalized.This method can be used to analyze a missile with control system for aero-servo-elas- tic divergence.This method preserves the advantages of original method in reference[1],that is,fuselage structure as input dada,and the mathemetics theory reguired is simple.
出处
《战术导弹技术》
1995年第1期6-14,共9页
Tactical Missile Technology
