国防科技大学学报2018，Vol.40Issue(2)：28-34,7.DOI:10.11887/j.cn.201802005
考虑扰动引力影响的弹道助推段误差传播解析计算方法
Analytical expression of error propagation along powered phase trajectory of missile by disturbing gravity
摘要
Abstract
Regarding the influence to the inertial navigation system of missile by disturbing gravity was focused,a polynomial fitting method was used to express disturbing gravity along the trajectory, and an analytical expression for calculating the deviation from the nominal value without considering disturbing gravity was deduced based on the linear system theory and the perturbation theory.Moreover,the coupling property between disturbing gravity and apparent acceleration was considered.The apparent acceleration deviation caused by disturbing gravity was regarded as an additional term of disturbing gravity, and was corrected by iterative method.The simulation results show that the error of disturbing gravity fitting method is less than 3 ×10 -7m/s2, and the residual error of the analytical formula considering the compensation of the apparent acceleration deviation is about 1/3 of the original method, and the computation time is only 1/10 of the numerical integration method.关键词
状态空间摄动法/多项式拟合/弹道助推段/解析解/扰动引力Key words
state space perturbation method/polynomial fitting/powered phase trajectory of missile/analytical expression/disturbing gravity分类
航空航天引用本文复制引用
王磊,郑伟,周祥..考虑扰动引力影响的弹道助推段误差传播解析计算方法[J].国防科技大学学报,2018,40(2):28-34,7.基金项目
国家部委基金资助项目(613222) （613222）
