摘要
针对近地航天器故障模式或深空探测模式,研究了仅利用太阳敏感器和陀螺进行航天器定姿的方法。给出了姿态确定滤波模型,分析了影响定姿精度的主要因素,讨论了轨道日照角对定姿精度的影响。研究结果表明:该组合可实现航天器故障模式或深空探测模式中的低精度姿态确定;轨道日照角对定姿精度影响较大,有效的轨道日照角是确保太阳敏感器/陀螺姿态确定方法可行的关键。
The method that only using the sun sensors/gyro to determine the attitude for low earth spacecraft failure and deep exploration was put forward in this paper. The attitude determination filtering model was given out. The main influence factors of attitude determination accuracy were analyzed. The influence of orbit sunangle for attitude determination accuracy was discussed. The results showed that this combination could meet the low attitude determination accuracy for spacecraft failure and deep exploration mode, but orbit sunangle had a large influence on the attitude determination accuracy. Effective orbit sunangle was the feasible key to ensure sun sensors/gyro attitude determination method.
出处
《上海航天》
2013年第1期36-43,共8页
Aerospace Shanghai
关键词
深空探测
太阳敏感器
陀螺
轨道日照角
定姿精度
Deep exploration
Sun sensors/gyro
Sunangle
Attitude determination accuracy
