基于驱动机构作动的太阳翼振动控制原理与实验研究

针对航天器在调姿或变轨过程中太阳翼长时间、低频振动引起航天器系统无法正常工作的问题,以太阳翼自身驱动机构为作动器,提供反馈控制力,进行振动抑制。在原理性研究的基础上,建立了贴近工程实际的真实尺寸太阳翼有限元模型,改进了控制算法,实现了太阳翼在振动控制结束后的正确复位,并利用动力学缩比模型对振动抑制方法的有效性开展了实验验证。结果表明:该方法不需引入额外的非有效载荷,能够在保证太阳翼不偏离目标位置的同时,有效抑制太阳翼的低频振动。

Principle and Experiment Study of Vibration Control in Solar Array Based on Actuating Mechanism

For the problem that spacecraft system cannot work normally caused by long time low-frequency vibration in solar array during the process of spacecraft attitude adjustment or orbital maneuver, the driving mechanism is taken as the actuator, providing feedback control force to suppress the vibration. Based on the principle study, the real-size solar array finite element model is established. By improving the original algorithm, the solar array can return to target position after vibration control. In addition, the effectiveness of the low-frequency vibration suppression method of the solar array is verified experimentally by dynamic scaled model. The result shows that without introducing extra load, the control method can ensure that the solar array does not deviate from target position and can suppress the vibration effectively.