弹道导弹天文/惯性导航误差修正方法研究

Research on the Error Correction Algorithm of Ballistic Missile CNS/INS Integrated Navigation

通过分析导弹天文导航和惯性导航的导航原理和误差模型,在基于充分利用高精度天文导航参数的思想上,提出了组合导航的误差修正方法。首先对两种导航参数进行了归算,而后提出了利用多次的天文测量参数对惯性测量误差进行修正的方法。该方法能较为准确地分离出引起射程误差较大的关机点速度、位置等的误差值,从而为实现利用天文导航进行射程误差修正提供前提条件。仿真计算表明,该方法是行之有效的。

Based on the ideal of making most use of the celestial navigation system （CNS） that is high accuracy, after analyzing the principle and error models of the CNS and inertial navigation system（INS）, an error correction algorithm of the CNS/INS integrated navigation is presented. The first part of this paper is the reducing calculus of the CNS parameter and the INS parameter. Then, the approach using the multiple metering parameters of celestial navigation system to correct the inertial navigation parameter is introduced. This approach can accurately separate the errors which would cause the bigger landing error from flying parameters, such as velocity and position. Then the landing error correct is implemented by the integrated navigation. It is easy to see that the approach can improve the hit probability of the ballistic missile. At last, the simulation calculation shows that the algorithm is available.