基于GPS伪距的火箭弹扰动源最优估计方法  

Optimal Estimation of Disturbance Source Based on GPS Pseudo-Distance for Rockets

作　　者：卞伟伟[1] 王良明[1] 丁传炳[2] 

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

出　　处：《计算机仿真》2013年第3期80-83,共4页Computer Simulation

基　　金：2011年高等学校博士学科点专项科研基金资助课题(20113219120030)

摘　　要：针对某型火箭弹纵向运动过程,根据小扰动运动理论,采用"系数冻结法"推导出了火箭弹纵向扰动运动的解析方程。根据风洞吹风实验数据,采用拟合的方法给出弹体纵向运动气动参数模型,建立了以气动系数误差扰动源和GPS误差源为状态量的系统状态方程,利用GPS伪距观测量构建了系统量测方程,应用扩展卡尔曼滤波方法对火箭弹被动段纵向平面的气动参数误差干扰源进行最优估计和仿真。仿真结果表明,改进方法加快了扰动源误差的收敛速度,并提高了估计精度。Aiming at the longitudinal movement of rocket projectile and according to the small perturbation motion theory, the analytical equations of longitudinal disturbance movement were derived by adopting ＂coefficient freezing way＂. The projectile body longitudinal aerodynamic parameters were fitted out with wind tunnel experimental data. Taking aerodynamic coefficients errors disturbance source and GPS error sources as state variables, the system state e- quations were established. And the system measurement equations adopted GPS pseudo-distance measurements. In trajectory passive segment, an optimal estimation and simulation on the aerodynamic coefficients disturbance errors sources of longitudinal movement were implemented with extended Kalman filter. The results show that the method can accelerate the convergence speed of the disturbance source errors and improve the estimation accuracy.

关 键 词：制导火箭弹 扰动 伪距 纵向运动 卡尔曼滤波 

分 类 号：TJ413.6[兵器科学与技术—火炮、自动武器与弹药工程]