基于扩展卡尔曼滤波的卫星组合姿态确定物理仿真技术研究

Research on Satellites Integrated Attitude Determination Physical Simulation Based on Extended Kalman Filter[HS)]

摘要:

针对未来卫星应用的高精度、高可靠性定姿技术需求,设计了卫星单轴组合姿态确定物理仿真系统；采用太阳敏感器和光纤陀螺组合定姿模式,提出了一种扩展卡尔曼滤波组合姿态确定算法,用C语言进行了实验软件设计,系统采用DSP为处理器,还设计了多敏感器数据采集扩展接口；物理仿真实验结果:姿态确定精度优于0.5°；陀螺常值漂移估计的平均值为3.625758e-4°/s,证明了组合姿态确定算法的有效性和该项技术对工程应用的可行性。

Abstract:

For the requirement of high accuracy and high reliability attitude determination of coming satellites applications, the single-axis spacecrafts attitude determination physical simulation system was designed. For the sun sensors and gyros integrated mode, an attitude determination algorithm based on the extended Kalman filter was proposed. The software was designed by C language. The system was based on DSP, and a multi sensors data interface was designed. The physical Simulation results:attitude determination accuracy of better than 0.5°. The gyro constant drift estimated average of 3.625758e-4°/s, the experimental results show the effectiveness of the algorithm Attitude Determination and application of the technology for the engineering feasibility.