挠性航天器振动抑制的自适应方法及实验研究

Adaptive Control Scheme and Experiment for Vibration Suppression of Flexible Spacecraft

挠性航天器在平衡位置的小幅度振动对航天器的姿态控制精度具有严重影响,并且难以控制。现介绍了一种带有非线性阻尼器的自适应控制方法。该方法在黄金分割自适应控制方法的基础上,通过引入振动能量阻尼项得到了比较理想的振动抑制效果。该方法能够快速地抑制挠性航天器的低频振动,并且具有很好的过渡过程品质和稳态精度。文章最后通过物理仿真对比实验验证了这种方法的有效性。在相同条件下,其振动抑制的时间较传统方法减少了70%。此外,该控制方法对航天器的挠性振动频率的变化具有很好的适应能力。

The low amplitude vibration near the equilibrium point, which is harmful for attitude control accuracy, is hard to be damped. In this paper an adaptive control law with a nonlinear damper was given out. The nonlinear adaptive control law with a vibration energy damper, designed based on 'golden section adaptive control law', can not only increase the vibration damping but also remarkably damp the remainder vibration near the equilibrium point. The validity of this scheme was validated by physical simulation at last. This control scheme can damp the vibration faster (70%) than traditional control schemes and can adapt the variations of the vibration frequency.