离心机试验中惯导平台误差系数辨识方法  

Error parameters identification for inertial navigation platform based on centrifuge test

作　　者：许永飞[1] 张士峰[1] 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2017年第1期46-50,共5页Journal of National University of Defense Technology

摘　　要：针对离心机试验中惯导平台误差系数辨识问题,提出一种6位置辨识方案。建立误差系数辨识的非线性模型,再利用扩展卡尔曼滤波估计误差系数。由滤波中的估值方差矩阵计算各误差系数之间的相关系数,用相关系数分析系统的可观性,并将所有相关系数之和最小作为优化指标,利用遗传算法得到最优的位置组合。仿真结果表明,采用该方案可以有效辨识出惯导平台中与加速度高阶项有关的各项误差系数。In order to identify the error parameters of inertial navigation platform in the centrifuge testing, a 6-position identification scheme was developed. The non-linear model of the inertial navigation platform for the identification was established, and the extended Kalman filter algorithm was applied to estimate the error parameters. The correlation coefficients among the error parameters calculated with the estimation error covariance matrix in the filter were used to analyze the observability of the system. The minimum sum of all correlation coefficients was considered as the optimization criterion, and then the genetic algorithm was utilized to obtain the optimal position combination. The simulation results show that the scheme is valid to identify all the error coefficients connected with the higher-order acceleration with high precision.

关 键 词：惯导平台 离心机试验 相关系数 参数辨识 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]