某型末制导炮弹惯导段弹道对气动参数灵敏度分析  

A Sensitivity Analysis of Effect of Trajectory of the Terminal Guidance Projectile on the Aerodynamic Parameter

作　　者：唐成荣[1] 宋卫东[1] 郭博[1] 侠文强[1] 

机构地区：[1]军械工程学院,石家庄050003

出　　处：《价值工程》2010年第31期167-168,共2页Value Engineering

摘　　要：目前的灵敏度分析往往需要依赖于某种寻优算法,并要求目标函数能求取偏导数。而末制导炮弹左右舵片上的控制力是突变的,无法对其求取偏导数。为解决这个问题并保证灵敏度分析精度,本文提出用解析法与有限差分法法有机结合的方法对气动参数进行灵敏度分析。结果表明,该方法能很好的解决了该弹道灵敏度分析问题,且分析速度快、精度高。At present,the method of sensitivity analysis depends on a algorithmic optimization,and asks to be can compute differential coefficient of the target function. The control power of right and left rudders of the terminal guidance projectile is saltation,so the function can not be computed differential coefficient. To solve this question and assure the analysis precision,this article uses the analytic method combines the limited difference method,to gain the sensitivity of the aerodynamic parameter. The results show that this method can well solve the sensitivity analysis of this trajectory,and the analysis is fast and precision.

关 键 词：末制导炮弹 气动参数 灵敏度 

分 类 号：TJ013.2[兵器科学与技术—兵器发射理论与技术]