ASUKF方法在航天器自主导航中的应用  

Application of ASUKF in autonomous spacecraft navigation

作　　者：李璟璟[1] 张迎春[1,2] 李化义[1] 陈雪芹[1] 

机构地区：[1]哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨150001 [2]深圳航天东方红海特卫星有限公司,广东深圳518057

出　　处：《哈尔滨工程大学学报》2011年第5期575-580,共6页Journal of Harbin Engineering University

基　　金：国家高技术研究发展计划基金资助项目(2008AA702101);国家自然科学基金资助项目(60904051)

摘　　要：针对自主导航过程中不确定的测量噪声和干扰的影响,提出了一种具有自适应能力的状态估计方法———ASUKF方法.该方法对非线性的状态方程进行超球面分布UT变换,对非线性的测量方程求取雅可比矩阵,同时在滤波迭代过程中引入自适应因子,从而在保持估计精度的条件下,降低了UKF算法的计算量,并使滤波器具有了自适应能力.将ASUKF方法应用于自主导航系统导航信息的估计过程中,仿真结果表明:其在保持导航信息估计精度的同时,提高了估计效率,克服了自主导航过程中不确定的噪声和随机干扰的影响.In order to overcome uncertain noise and disturbance during autonomous spacecraft navigation,a state estimation method known as angmented state unscented kalman filter（ASUKF） having adaptive ability was presented.This method applied spherical simplex unscented transformation in the nonlinear state equation,calculated the Jacobian matrix in the nonlinear measurement equation,and introduced the adaptive factor during the filtering process.This was done to keep estimation precision the same as unscented kalman filter（UKF）,reduce scalar calculation,and improve the adaptive ability.Applying the ASUKF method to an autonomous navigation system through simulation shows that ASUKF not only retains estimate precision of navigational information,but also enhances estimation efficiency and has the ability to adapt to uncertain noises and random disturbances.

关 键 词：ASUKF 非线性 SSUT 自适应 自主导航 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]