航天器主动振动反馈全物理仿真试验研究

Physical Simulation Experiment for Flexible Satellite Control with Vibration Information Feedback

以具有大面积太阳帆板的挠性航天器为工程背景,以挠性航天器全物理仿真系统为实验平台,提出了主动引入挠性振动信息的航天器振动抑制控制方案。建立了挠性帆板顶端加速度计的测量模型,设计了自适应滤波器进行加速度计数据处理,并将该挠性振动加速度引入航天器姿态控制,进行了大角度机动全物理仿真试验。中心刚体进行25°大角度机动,机动过程平稳,机动结束后姿态指向精度达到0.01°,帆板顶端加速度在0.15m/s2以内,一阶振型的振幅为0.015m/s2。全物理仿真试验验证了基于振动加速度反馈的控制方案能够有效地抑制挠性振动。系统仅在挠性帆板顶端增加了一个微型加速度计,结构简单,控制方案可用于实时控制。

The attitude control for large flexible spacecrafts is a key issue in space technology.Satellites with large flexible solar panels are taken as practical background.A physical simulation system for flexible satellite is used as an experiment test-bed.Vibration suppression control with flexible vibration acceleration feedback is promoted.A small accelerometer is placed at the end of the flexible penal,the measurement model of this accelerometer is established and an adaptive filter is designed for its data procession.Feedback control using the vibration information from the acceleration signal is designed.Large angle maneuver experiment is carried out.The centre body maneuvers about 25° smoothly and the precision of the attitude after maneuver is within 0.01°.The acceleration at the end point of the flexible panel during the experiment is within 0.15 m/s2,and the altitude of the first mode is 0.015 m/s2.Compared with classical PD control,physical simulation experiments verify that the control scheme with vibration information feedback can suppress flexible vibration more effectively.Only a small accelerometer is placed on the flexible panel,the control system is simple and the control scheme can be carried out in real time system.