摘要
针对固体运载火箭发动机能量不可控及喷管控制精度有限导致的关机点轨道参数精度较低问题,提出一种基于修正牛顿迭代的固体运载火箭末修级入轨制导方法。首先,直接建立目标轨道参数与制导变量的非线性方程。然后,通过引入修正系数矩阵并采用牛顿迭代方法保证偏导矩阵范数逐次递减,提高了制导精度及迭代收敛性。仿真结果表明所提方法相对闭路制导,轨道半长轴偏差平均降低101.2 m、1 km以内入轨概率提高8.52%,工程适用性较强。
Aiming at the low precision of orbital parameters at shutdown point caused by uncontrollable energy of solid launch vehicle engine and limited nozzle control precision,a terminal correction guidance method of solid rocket based on modified Newton iteration is proposed.First,a nonlinear equation between target orbital parameters and control variables is established.Then,the guidance precision and range of convergence are improved by introducing the correction coefficient matrix and Newton's iteration method to ensure that the norm of partial derivative matrix decreases successively.The simulation results show that compared with closed loop guidance,the proposed method reduces the semi-major axis deviation by 101.2 m on average,and improves the probability of orbit entry within 1 km by 8.52%,showing strong engineering applicability.
作者
葛云鹏
梁卓
吕瑞
涂海峰
陈喆
GE Yunpeng;LIANG Zhuo;LV Rui;TU Haifeng;CHEN Zhe(China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《中国惯性技术学报》
EI
CSCD
北大核心
2021年第4期549-553,共5页
Journal of Chinese Inertial Technology
基金
装备发展领域基金(41412050)。
关键词
固体火箭
牛顿迭代
末修
制导
solid rocket
Newton iteration method
terminal correction
guidance
