导弹气动伺服弹性稳定性分析

导弹气动伺服弹性稳定性分析是导弹受控舵面设计的一个重要问题。针对防空导弹的特点 ,采用气动力导数加下洗修正的非定常气动力方法来计算其气动力。在气动弹性运动方程的建立和气动弹性环节传递函数的确定上 ,采用了传统的主模态法 ,在此基础上 ,利用乃奎斯特法对导弹进行了气动伺服弹性稳定性分析和稳定裕度分析。

Analysis of Pneumatic Servo Elastic Stability for Missile

Analysis of Pneumatic servo elastic stability for missile is an important problem of designing for controlled rudder.According to the characteristic of antiaircraft missile,the non localized aerodynamic criterion with aerodynamic derivative and downriver correction is applied to calculate the aerodynamic force in this paper. With the traditional mainmoda,this paper builds up the kinematical equation and determinates the transfer function of aeroelasticity link.Based on that,the pneumatic servo elastic stability and margin of stability for missile is analyzed with Nyquist method.