GPS/INS组合制导弹药空中对准的初始滚转角估计新算法  

New Algorithms to Estimate Initial Roll Angle for In-flight Alignment of GPS/INS Guided Munitions

作　　者：佘浩平[1] 杨树兴[1] 倪慧[2] 

机构地区：[1]北京理工大学飞行器动力学与控制教育部重点实验室,北京100081 [2]中国兵器科学研究院,北京100089

出　　处：《兵工学报》2011年第10期1265-1270,共6页Acta Armamentarii

基　　金：国防基础科研项目(B2220060060)

摘　　要：GPS/INS组合制导弹药从常规平台发射后需要在空中重新对准时,滚转角的初值难以获得。为解决该问题,分别针对弹体倾斜稳定和低速旋转两种情况,提出了估计初始滚转角的新算法。从姿态运动学方程出发,推导了弹体滚转角与横向角速率、姿态角速率之间的关系式,利用角速率陀螺测量值和GPS的速度测量值,基于最小二乘估计方法,可获得滚转角的最优估计值。仿真结果和性能分析表明,飞行过程中的随机风和常值风是影响估计精度的主要因素,在各种典型测量水平和飞行条件下估计算法的误差均小于3°.该算法可用于空中粗对准时的滚转角估计。When GPS/INS guided munition needs in-flight realignment after it is fired from a conventional platform, an initial roll angle is difficult to be acquired. To solve this problem, two new algorithms of initial roll angle were proposed with regard to the non-spin and low-speed spin of projectile. The relationships between the roll angle and the transverse angular rates and attitude angle rates were derived from attitude kinematics equations. The measured values of angular rate gyroscopes and GPS velocity were used to obtain optimal estimation of roll angle based on least squares estimation. Simulation resuhs and performance analysis show that the random and constant wind during flight are the main factors affecting estimation accuracy. The estimated errors are less than 3° under different typical levels of measurement and flight conditions. The algorithm can be used to estimate the roll angle during in-flight coarse alignment.

关 键 词：飞行器控制 导航技术 制导弹药 惯性导航系统 空中对准 滚转角 

分 类 号：TJ765.23[兵器科学与技术—武器系统与运用工程]