机动发射条件下助推滑翔导弹射击诸元快速解算  

Efficient method for firing data calculation of boost-glide missile in mobile condition

作　　者：何睿智[1] 刘鲁华[1] 汤国建[1] 包为民[1,2] HE Ruizhi LIU Luhua TANG Guojian BAO Weimin(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China China Aerospace Science and Technology Corporation, Beijing 100048, China)

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 [2]中国航天科技集团公司,北京100048

出　　处：《国防科技大学学报》2017年第4期56-61,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(11502289)

摘　　要：针对机动发射条件下助推滑翔导弹对全程弹道快速生成的迫切需求,在弹道设计中选取7个关键性控制量参数作为全程弹道射击诸元,并提出与之相对应的诸元解算算法。将全程弹道分为助推段、初始下降段、滑翔段和俯冲攻击段,在统一化运动模型描述的基础上,运用参数化迭代的思路,依次对不同飞行阶段诸元进行了快速求解,满足多种复杂约束条件。在全程诸元迭代解算模式的基础上,提出助推段沿用中心弹道诸元,仅对其他射击诸元进行重计算的部分诸元迭代解算模式。仿真结果表明:采用所提助推滑翔导弹射击诸元快速解算方法,可在大范围机动条件下对远距离地面固定目标进行快速精确打击。Considering the urgent need of rapid trajectory generation of boost-glide missile in mobile condition,seven key parameters of control variables were selected as the firing data,and the corresponding iterative calculation algorithms were proposed. The full-range trajectory was divided into the boost phase,initial phase,glide phase and dive attack phase,all these flight phases were described in a unified dynamics model. Firing data in different phases were calculated rapidly one by one,and multiple constraints were satisfied strictly,with the help of the parameterized iterative algorithm. Furthermore,a partly recalculation mode which uses the firing data of the center trajectory in the boost phase and recalculates the others was proposed on the basis of the full mode. The simulation results indicate that this method can achieve a great performance in the quick attack to a ground stationary target in mobile condition.

关 键 词：助推滑翔导弹 机动发射 全程弹道 诸元解算 

分 类 号：V448[航空宇航科学与技术—飞行器设计]