摘要
卫星三轴姿态的确定是对卫星进行姿态控制的基础,利用陀螺和红外敏感器互补的特性,并对测量所得到的数据进行处理,便可得到卫星姿态角的估计值。陀螺和红外地球敏感器是卫星姿态控制系统中关键的测量部件,两者的测量输出通过卫星运动学方程相关,有冗余关系,可以用于故障检测。本文对所设计的观测器进行了数值仿真,证实了其有效性,并直接利用所设计的观测器进行故障检测,首先得出陀螺和红外地球敏感器在各种故障下的输出残差曲线,然后分析陀螺和红外地球敏感器的不同故障对输出残差信号的不同影响,找出各种故障与不同输出残差的对应关系,从而确定发生故障的部件。
The three-axis attitude determination is the basis of satellite attitude control. By using of the complementary characteristics of gyros and infrared earth sensors and processing the acquired data, the satellite attitude estimation is obtained. The measured values of gyros and infrared earth sensors are correlated through satellite kinematics equation, which can be used for fault detection. In this paper, the validity of the designed observer is approved by simulation. And then use the designed observer to detect faults. First this paper gets the output error in the presence of fault of gyros and infrared earth sensors, and then analyzes the different influence of fault of gyros and infrared earth sensors on the error and finds the relations of fault and different errors. So the fault can be isolated.
出处
《航天控制》
CSCD
北大核心
2007年第2期78-81,共4页
Aerospace Control
关键词
姿态确定
观测器
故障诊断
输出残差
Attitude determination
Observer
Fault diagnosis
Output error
