弹道导弹中段机动突防发动机总体优化设计  

System optimization design of maneuver penetration motor in the midcourse of ballistic missile

作　　者：吴启星[1] 王祖尧[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2007年第4期278-281,286,共5页Journal of Solid Rocket Technology

摘　　要：针对弹道导弹中段机动突防,提出了一种突防方案的发动机总体参数优化设计。从中段机动突防运动学、动力学出发,基于战术需求明确突防发动机优化设计指标,采用进化算法进行了发动机总体参数优化,并给出了仿真算例。研究表明,速度增量大小和机动时刻给定时,零控脱靶量随速度增量方向的不同存在极小值和极大值,极大值方向近似垂直于视线方向,且最大值近似为待飞时间和速度增量大小的乘积,发动机设计总冲指标即在此理论推导上获取;进化算法有效地解决了8个设计变量、3个约束条件的突防发动机参数优化问题,优化结果合理,且实现了战术要求的脱靶量,很好地满足了弹道导弹中段机动突防对动力系统的要求。Aiming at midcourse maneuver penetration of ballistic missile, optimization design of system parameters of motor used for a penetration scheme was put forward. Proceeding from midcourse maneuver penetration kinematics and dynamics, optimization design indexes were determined on the basis of tactical requirement. System optimization design of motor was conducted by means of evolutionary algorithm, and simulation calculation cases were given. The investigation results show that when the velocity increment and maneuver time are given,there exist the maximum and minimum values of zero effort miss steering along the velocity increment direction, and direction of the maximum value is vertical to that of sight line, moreover the maximum value is approximately equal to product of await flying time and velocity increment. Total impulse of motor design was obtained on the basis of theoretical derivation, and evolutionary algorithm is used for parameter optimization design of penetration motor with eight design variables and three constrains. The optimization results are rational, which realize tactical requirement of the miss distance and meet demand of dynamic system for midcourse maneuver penetration of ballistic missile.

关 键 词：弹道导弹 中段机动突防 零控脱靶量 进化算法 发动机优化设计 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]