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本文讨论远程弹道导弹惯性制导系统的误差传播特性。导出了惯导系统转移矩阵的解析解,用回归分析方法建立了干扰模型,在此基础上推得落点偏差解析表达武。 利用解析解对惯导系统进行误差分析无需解微分方程组。为了解算落点偏差,只需用代数方法确定干扰系数和误差传播系数。 最后,对42条弹道的试算结果表明,解析解的最大误差小于10米。
This article discusses the error propagation characteristics of the long-range ballistic missile inertial guidance system. The analytic solution of the inertial navigation system transfer matrix is derived, and the interference model is established by regression analysis. Based on this, the analytic expression of fall point deviation is deduced. There is no need to solve differential equations with analytic solution for error analysis of INS. In order to solve the landing error, only algebraic method to determine the interference coefficient and error propagation factor. Finally, the test results of 42 trajectories show that the maximum error of the analytical solution is less than 10 meters.