摘要
在导弹末制导阶段,结合自适应UKF滤波方法和直接滤波模型实现惯导/被动导引头组合导航,以提高惯导系统定位精度。首先采用惯导参数和导引头视线信息建立非线性模型,然后结合模型特点对UKF滤波流程进行简化,并针对系统状态变化较快和量测噪声不稳定的特点给出改进的自适应UKF滤波方法,能实现视线信息辅助修正惯导系统位置误差。仿真结果表明,该滤波方法具有较高的估计精度和较快的收敛速度,7s时惯导/被动导引头组合定位误差不高于30m。
To the location accuracy of improve inertial navigation system （INS）, a INS/passive seeker integrated navigation was realized using a combination of UKF and a direct filtering model in the stage of the terminal guidance of missiles. A nonlinear model was established with parameters of INS and the sight information of seeker. The UKF algorithmic framework was simplified based on the model features and an adaptive filter method was put forward for the fast change of state and the instability of measuring noises. This method can realize missile INS location error modifi- cation. Simulation results show that this filter method converges fast with high convergence accuracy, and the location error can be reduced to less than 30 meters at 7 seconds.
出处
《计算机仿真》
CSCD
北大核心
2015年第5期79-85,共7页
Computer Simulation
关键词
末制导
惯导
被动导引头
位置误差
Terminal guidance
INS
Passive seeker
Location error
