敏感器正常和故障模式下微小卫星的姿态确定方法

围绕某日-地空间环境组网探测系统中微小卫星定姿系统的设计需求,基于MEMS陀螺、小型CMOS太阳敏感器、微磁强计,研究了该微小卫星各敏感器正常工作模式以及敏感器故障模式下的系统建模和姿态确定方法。各敏感器正常工作模式下,用陀螺、太阳敏感器和磁强计进行组合定姿;陀螺故障时,用太阳敏感器和磁强计进行组合定姿;太阳敏感器故障时,用陀螺和磁强计进行组合定姿;陀螺/太阳敏感器同时故障时,用磁强计进行定姿。仿真结果表明,本文定姿方法的姿态确定精度满足该系统中微小卫星在轨运行时的定姿精度要求,为该微小卫星的半物理仿真系统的研究及其在轨运行时的姿态确定提供了依据。

Attitude determination method of micro satellite under normal and failure mode of sensor

With respect to the design requirement of attitude determination system of a micro-satellite for space > environment exploration, the method of system modeling and attitude determination are studied based on MEMS gyro, micro CMOS sun sensor and micro-magnetometer. The gyro, sun sensor and magnetometer are used for attitude determination under normal mode. The sun sensor and magnetometer are used under gyro failure mode. The gyro and magnetometer are used under sun sensor failure mode. The magnetometer is used under sun-sensor/gyro failure mode. Simulation results show that the attitude determination accuracy obtained by the provided attitude determination algorithm satisfies the attitude determination requirement of the micro-satellite, which provide the support for the micro-satellite's attitude determination and the research of its semi-physical simulation system.