变后掠翼导弹制导精度研究(英文)  

A Study on Guidance Precision of Missile with Alterable Sweep Wings

作　　者：周军[1] 张天翼[1] 郭建国[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《火力与指挥控制》2012年第8期39-43,46,共6页Fire Control & Command Control

基　　金：航天支持基金(N11XW0001);西北工业大学基础研究基金资助项目(JC201024)

摘　　要：将飞行器变后掠翼技术应用于导弹上,弹翼的运动对弹体动态特性与整个系统的制导精度会直接产生影响。首先基于多刚体动力学原理获得的变后掠翼导弹完整的数学模型,通过小扰动线性化方法得到了弹体相关的传递函数,并利用统计线性化方法计算了制导数学模型的均值与协方差传播方程,最后应用协方差分析描述函数方法分析得到了导弹的弹翼转动速度、弹翼后掠角大小与弹翼转动时刻对制导精度影响的规律。This paper presents the movement of sweep wing of aircraft.The technical is applied in missile and wing＇s movement will influence missile＇s dynamic characteristic and system＇s guidance precision directly.Firstly,the multi-body dynamic model for the whole missile is built with linear disposal,and utilize statistic linearization method calculate the guidance model＇s mean and covariance transmit equations by considering the interaction between the motion of the wings and the body,Finally,the disciplinarian is received by the method of covariance analysis describing function technique method analysis of the missile wing＇s turning speed,sweepback magnitude and turning time cause influence on the missile＇s guidance precision.

关 键 词：复合制导与控制 俯仰平面 蒙特卡洛方法 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]