扰动引力场中机动突防导弹落点精确预报方法  

Accurate Prediction Method of Impact Point for Maneuver Penetration Missiles in Gravity Anomaly Field

作　　者：王磊[1] 周祥 赵卫虎 程先哲 郑伟[2] WANG Lei;ZHOU Xiang;ZHAO Weihu;CHENG Xianzhe;ZHENG Wei(College of Information and Communication,National University of Defense Technology,Wuhan 430000,China;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学信息通信学院,武汉430000 [2]国防科技大学空天科学学院,长沙410073

出　　处：《南京航空航天大学学报》2024年第6期1090-1096,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金项目(12402420,62303479)。

摘　　要：针对弹道导弹大机动突防后精确制导面临的落点预测需求,提出了一种考虑高阶扰动引力影响的导弹落点解析预报模型。将落点预报问题分解为标准落点预报和落点偏差预报两部分,标准落点预报由二体椭圆轨道理论解析求解,落点偏差预报通过构建的状态空间摄动模型进行求解。基于球谐函数换极法建立高阶扰动引力矢量在轨道柱坐标系中的表达式,并推导得到由F函数和G函数等两类核函数组成的落点偏差预报解析模型以及F函数和G函数的递推公式。该模型无需射前准备工作,相对已有方法具有使用灵活、鲁棒性好等特点。数值仿真结果表明本文提出的落点预测模型残差均值为11.2 m,相对误差小于0.1%,预测耗时小于100 ms,能够为制导算法设计提供支撑,具有一定的工程应用价值。In view of the demand for impact point prediction of ballistic missiles in precise guidance after largescale maneuver penetration,an analytical missile impact point prediction model that considers the influence of high-order disturbing gravity is proposed.The impact point prediction problem is decomposed into two parts:Standard impact point prediction and impact point deviation prediction.The standard impact point prediction is directly solved by the two-body orbit theory,and the impact point deviation prediction is solved by the constructed state space perturbation model.The spherical harmonics pole-changing method is used to establish the expression of the high-order disturbing gravity vector in the orbit cylindrical coordinate system,and the analytical model for impact point deviation prediction composed of two types of kernel functions,such as F function and G function,is then derived,as well as the recursive formulas of F function and G function.This model does not require pre-launching preparations,and is more flexible in use and more robust than the existing methods.Numerical simulation results show that the average residual error of the impact point prediction model proposed in this paper is 11.2 m,the relative error is less than 0.1%,and the prediction time is less than 100 ms.It can provide support for the design of guidance algorithms and has certain engineering application value.

关 键 词：弹道导弹 机动突防 落点预测 解析摄动理论 扰动引力场 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]