作　　者： ; ; ;

机构地区： 国防科学技术大学理学院

出　　处： 《弹道学报》 2009年第4期1-5,共5页

摘　　要： 根据融合了干扰因素的再入机动弹头再入段六自由度弹道方程,研究了一种基于变化的再入干扰量偏导数矩阵和弹道参数偏差的参数估计方法,由再入干扰方程求得辅助导航系统开始工作前每一时刻的再入误差值.理论推导和仿真结果表明,该再入误差分析方法是合理的,分析结果在估算结果范围之内,气动干扰是再入误差的主要影响因素. The six-degree-of-freedom trajectory equations fused with interference factors for the reentry maneuvering warhead at the reentry phase were designed. A method for parameter estimation based on partial derivative matrixes and deflection of trajectory parameters was studied. The reentry error for each node before the work of aided navigation system was calculated by this method. Theoretical analysis and simulation indicate that the proposed method of reentry error analysis for reentry maneuver warhead is reasonable, and the analysis result is in the range of esti- mated results. The aerodynamic disturbance is the primary factor affecting reentry error.

关 键 词： 再入机动弹头 再入误差 辅助导航系统 误差分析 误差折合

领　　域： [航空宇航科学与技术] [航空宇航科学技术]