一种基于当地流活塞理论的超音速导弹气动伺服弹性分析方法  

An Aeroservoelastic Analysis Method for Supersonic Missiles Based on Local Piston Theory

作　　者：张陈安[1] 张伟伟[1] 叶正寅[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072

出　　处：《宇航学报》2007年第1期141-146,共6页Journal of Astronautics

基　　金：国家自然科学基金重点项目(10432040);航空科学基金(04A53006)

摘　　要：运用当地流活塞理论计算导弹的非定常气动力,在状态空间内实现了气动弹性系统与控制系统的耦合,并进行了时域分析。对某典型导弹的气动伺服弹性问题算例,计算了不同马赫数、不同迎角以及不同的传感器安装位置对导弹气动伺服弹性特性的影响,同时考察了控制系统的引入对不同刚度弹体气动伺服弹性特性的影响。算例结果与理论分析相吻合,表明该方法能简便的对全机、全弹复杂外形的气动伺服弹性正问题进行高效准确的分析,在较大范围的马赫数和迎角内都能得到可靠的结果。It is always difficult to analyze the aeroservoelastic stability of missiles or airplanes accurately and efficiently. The difficulty comes from two aspects： to calculate the aerodynamic forces accurately and efficiently, and couple the aeroelastic system with control system. Based on local piston theory, this paper coupled SISO control system with the aeroelastic system in the state space. Aeroservoelastic problem of a typical missile was analyzed with this method as the computational example. The influences of Mach number, angle of attack, structural filter and location of sensor on aeroservoelastic characteristics were examined. The impact of control system on rigid and flexible bodies was also studied. Reasonable results were attained in the conditions of Math number between 1.2 and 10, angle of attack up to 10 degrees. Results given by this method accorded with those given by theory analyses. With this method, the analysis of the aeroservoelastic characteristics for a missile or an airplane can be attained in a few minutes.

关 键 词：气动伺服弹性 颤振 当地流活塞理论 超音速 高超音速 降阶气动力模型 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]