摘要
为确保姿态测量器件长期在轨工作精度、提高姿态确定精度,针对典型的陀螺和星敏感器联合定姿方案,推导了一种星敏感器/陀螺在轨标定算法。考虑到卫星姿态测量过程中的几种主要误差源,建立星敏感器和陀螺标定模型,首先用递推算法对星敏感器单独在轨标定,然后采用Kalman滤波对星敏感器和陀螺同时进行在轨标定,对误差进行实时补偿,有效地提高了星敏感器和陀螺的测量精度,与同类算法相比,为卫星姿态确定提供了更加丰富的信息。最后对该算法进行了数学仿真,仿真结果验证了算法的有效性。
To ensure the long-term on-orbit working precision of attitude sensors, to meet the high accuracy of three-axis attitude determination of satellite, a real-time on-orbit calibration algorithm for gyros and star sensors is proposed . Considering several error sources during satellite attitude measure, a model of gyros and star sensors alignment error and scale factor error is constructed for compensating those errors. First of all it calibrates the star sensors, then it calibrates the gyros using the results of the first step. This algorithm can improve gyros＇ and star sensors＇ precision efficiently, comparing with the other calibration algorithms, it provides more information for satellite attitude determination, Simulation results indicate the availability and feasibility of the on-orbit calibration algorithm.
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2005年第12期2112-2116,共5页
Systems Engineering and Electronics
关键词
姿态确定
在轨标定
星敏感器
陀螺
attitude determination
on-orbit calibration
star sensor
gyros
