基于伪控制限制方法的再入航天器自适应控制

PCH Based Adaptative Control for Re-Entry Launch Vehicles

文中将基于伪控制限制方法的神经网络自适应控制运用到再入航天器的制导与控制中。利用两个控制回路来实现控制目标。其中,外回路适用于力的扰动,而内回路适用于力矩的扰动。限制外回路以阻止对内回路动态特性的调整,在达到控制极限时,伪控制限制也可进行自适应调整。另外,通过加入加速度计反馈元件来提高系统性能。

In this work, neural network adaptive flight control utilizing pseudo-control hedging method is applied to the guidance and control of re-entry launch vehicles. Two control loops are used to achieve this control strategy: the outer-loop adapts to force perturbations, while the inner-loop adapts to moment perturbations. PCH 'hedges' the outer-loop in order to prevent adaptation to inner-loop dynamics. The hedge also enables adaptation while at control limits. In addition, accelerometer feedback components are added into the system to improve its performance.