导弹尾罩分离运动不确定性分析  

Uncertainty analysis of the rocket trail cover separation

作　　者：贾如岩[1] 王涛[1] 江振宇[1] 胡凡[1] 张为华 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2014年第6期88-92,共5页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(51105368)

摘　　要：为了检验实际条件下导弹尾罩分离运动可能存在的风险,建立了基于凯恩方程的分离过程多体动力学模型与基于关键点-碰撞边界相对位置判断的碰撞检测模型,采用蒙特卡洛方法与Morris筛选法对输入参数存在随机偏差时尾罩分离运动受到的影响进行了不确定性分析,通过蒙特卡洛法得到了分离运动状态的散布特性,通过Morris筛选法得到了各输入变量的影响程度排序。研究结果表明:尾罩分离方案的可靠性较高,在输入参数存在偏差情况下也可满足安全性指标,各项输入参数中风干扰、推冲器的推力偏差对尾罩落点距离的影响相对较大,而导弹点火时尾罩的横向距离受风与出筒速度的影响相对较大。To assess the risk of the rocket trail cover separation movement,the multi-body dynamic model in separation process was established according to the Kane＇s equation,and the collision checking model based on the relative location estimation of the key point-collision boundary was built. The Monte Carlo method and the Morris screening method were used to analysis the uncertainty of the separation process when the input parameters had random deviations. The dispersion characteristics of the separation motion state were got from the Monte Carlo method and the sensitivity of each parameter was ranked by using the Morris screening method. Results show that the trail cover separation solutions possess high reliability,which can satisfy the security requirements in the case of the input parameters with deviations. Among all the input parameters,wind interference and the thrust deviation of the thruster from ejection pistons has greatly influenced the distance of drop points,and the horizontal distance between the rocket and the trail cover has been greatly affected by the wind and the out-canister velocity under the circumstances of ignition.

关 键 词：尾罩分离 不确定性分析 蒙特卡洛法 Morris筛选法 

分 类 号：V421[航空宇航科学与技术—飞行器设计]