星敏感器光轴测量的锥面误差模型及其应用  

Cone Measurement Error Model of Star-sensor's Optic Axis and Its Application

作　　者：矫媛媛[1] 周海银[1,2] 李新娜[1] 王炯琦[1] 潘晓刚[1] 

机构地区：[1]国防科技大学理学院数学与系统科学系,长沙410073 [2]空间智能控制技术国家级重点实验室,北京100190

出　　处：《宇航学报》2010年第9期2138-2144,共7页Journal of Astronautics

摘　　要：星敏感器是卫星高精度姿态测量系统中的重要器件,根据其测量可以建立不同形式的星敏感器测量模型,准确分析测量模型中测量误差的特性是保证卫星姿态确定精度的重要条件。本文针对广泛采用的星敏感器光轴矢量测量方程,从几何角度出发,结合实际情况,提出了一种新颖的星敏感器光轴测量的锥面误差模型。在两个锥面参数分别服从一定的概率分布的条件下,对测量误差特性进行了深入分析,确定出新的测量误差协方差矩阵。上述研究能够在不增加算法计算量的前提下,从新的角度,更为直观地建立了星敏感器光轴矢量测量模型。最后在仿真实验中,将新的锥面误差测量模型应用于基于扩展卡尔曼滤波(EKF)的姿态确定方法中,结果表明了利用该测量模型进行姿态确定的有效性。Star sensor is one of the most important sensors in satellite attitude measurement system.There are different kinds of star sensor＇s measurement models in application,and the exact measurement error model is essential for the accuracy of attitude determination.In this paper,a cone measurement error model for measurement vector of star sensor＇s optic axis is established based on the reasonable assumption.According to the cone parameters,the characteristics of the measurement error is analyzed and the new measurement error＇s variance matrix is derived.The measurement model of optic axis is constructed intuitively by the new cone measurement error model,and the computational effort is not increased.In simulation experiments,the new cone measurement error model is employed in the EKF based attitude determination method.Results show the validity of the new measurement model.

关 键 词：星敏感器 锥面误差模型 测量误差特性 姿态确定 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]