一种卫星反作用飞轮延寿方法  

Method of Lifetime Prolongation for Satellite Reaction Flywheel

作　　者：张国云[1] 王大鹏 蔡立锋[1] 张国雪[1] 张卫涛 ZHANG Guoyun;WANG Dapeng;CAI Lifeng;ZHANG Guoxue;ZHANG Weitao(Key Laboratory for Fault Diagnosis and Maintenance of Spacecraft in Orbit, Xi’an Satellite Control Center,Xi’an 710043,China)

机构地区：[1]西安卫星测控中心航天器在轨故障诊断与维修重点实验室,西安710043

出　　处：《航天器工程》2019年第1期42-47,共6页Spacecraft Engineering

摘　　要：针对反作用飞轮长时间工作出现的性能退化问题,提出一种反作用飞轮和磁力矩器联合控制使反作用飞轮延寿的方法。通过滚动轴在姿态机动模式下采用比例积分微分(PID)轮控,而在正常稳态模式下使用比例微分(PD)磁控,实现在不降低姿态控制精度的前提下减少反作用飞轮工作时间,从而延长其工作寿命的目标。对联合控制姿态的延寿方法进行仿真分析,验证滚动轴稳态磁控算法、磁控接入及退出条件的正确性。以某低轨卫星为例进行在轨验证,遥测数据显示:卫星正常运行2年多,滚动轴姿态超差最大约2.6°,且绝大部分时间均小于1°,卫星稳态情况下没有自主切换回PID轮控方式,飞轮因长期轴承摩擦引起的电流、温度增大趋势得到有效缓解,飞轮在轨寿命得到延长。In order to solve the problem of performance degradation of the reaction flywheels in the long time work,a method of reaction flywheel lifetime prolongation based on the joint control of reaction flywheels and magnetorquer is proposed.The method uses the PID wheel control in the attitude maneuver mode and uses PD magnetic control in the normal steady state mode,thus reducing the working time of the flywheel without reducing the attitude control precision.The correctness of the rolling axis steady state magnetic control algorithm and the specific principles of magnetic control access and exit conditions are verified by simulation analysis.A low orbit satellite is taken as an example.The telemetry data show that the satellite has been in normal operation for more than two years and the maximum attitude error of the rolling axis is about 2.6°,and most of the time is less than 1°,and there is no turn-back PID control mode in the case of satellite steady state.The method proposed can reduce the working time of the flywheel and effectively alleviate the increasing trend of the current and temperature caused by the friction of the long-run bearing flywheel,so the flywheel can prolongate lifetime.

关 键 词：卫星反作用飞轮 延寿 磁力矩器 联合控制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]