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分析了导弹SINS/CNS/GPS复合制导系统的缺点,设计了一种新的组合制导方案,该方案分三个阶段:SINS导航段、SINS/CNS导航段和SINS/CNS/GPS导航段。在最后导航段采用了联邦滤波器的结构。在发射惯性坐标系下分别建立SINS/CNS和SINS/GPS子系统状态方程和观测方程,分别设计了UKF和KF滤波器,在数据融合前,先通过一致性检验判断GPS的干扰,然后采用信息分配原则进行数据融合。仿真实验表明该方案有较好的效果和适应能力。
The shortcomings of missile SINS / CNS / GPS composite guidance system are analyzed and a new combined guidance scheme is designed. The scheme consists of three phases: SINS navigation segment, SINS / CNS navigation segment and SINS / CNS / GPS navigation segment. The structure of the federal filter is used in the final navigation section. The SINS / CNS and SINS / GPS subsystem state equations and observation equations are respectively established in the launching inertial coordinate system, and the UKF and KF filters are designed respectively. Before the data fusion, GPS interference is judged through the consistency test, and then the information Distribution principle for data fusion. Simulation experiments show that the program has good effect and adaptability.