滑翔增程弹导航系统误差修正方法研究  

Study on Error Correction Method for Navigation System of Gliding Extended-range Projectile

作　　者：李岩[1] 王中原[1] 丁传炳 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094 [2]中国舰船研究中心,上海201108

出　　处：《弹道学报》2012年第4期18-21,共4页Journal of Ballistics

基　　金：高等学校博士学科点专项科研基金项目(20113219120030)

摘　　要：为了提高滑翔增程制导炮弹的姿态测量精度,分析了单GPS天线测量弹体姿态角的计算方法,应用GPS和INS全组合的方式,采用INS和GPS的位置、速度和姿态误差信息作为观测量,设计了卡尔曼滤波器,将滤波估计的结果反馈给INS,实现对测量系统全参数的误差修正.数值计算和仿真结果表明,采用基于GPS姿态测量信息的Kalman滤波方法,对INS惯导系统测量误差进行修正,降低了3个姿态角的测量误差,加快了系统误差收敛速度,提高了滑翔控制系统的控制精度,增加了制导炮弹滑翔增程的效果.To improve the attitude measurement precision of gliding extended-range guided projectile （GERGP）, the attitude-angle calculation-method based on single-antenna GPS measurement was analyzed. To realize the full parameters errors correction,a Kalman filter with position,velocity, attitude errors from GPS/INS was designed, and the estimated results were adopted as the INS feedback. The numerical calculation and simulation show that it can reduce the three attitude-angles of the system and quicken the error constringency speed to apply Kalman filter based on GSP attitude-angle measurement to correct INS attitude-angles errors, and the control precision and gliding extended-range effect of GERGP were improved.

关 键 词：滑翔增程 误差修正 姿态测量 KALMAN滤波 

分 类 号：TJ413.6[兵器科学与技术—火炮、自动武器与弹药工程]