Attitude manoeuvre and vibration control of flexible spacecraft using computed feed-forward input commands and proportional-derivative feedback

Abstract

The current paper presents an investigation into development of feed-forward and feedback control strategies for active vibration and attitude control of a flexible spacecraft. In this approach, the feed-forward loop consists of a computed-torque scheme and a command shaping technique based on component synthesis vibration suppression (CSVS) method for shaping the input signal. For relaxing the requirement of dynamic linearity in traditional CSVS, a new approach is developed for designing the input component command by utilizing a structure, in which the modal forces of flexible modes vibration are shaped according to a predefined trajectory, to achieve the vibration suppression for the non-linear attitude dynamics. In addition, to follow the predefined trajectory identically or at least as closely as possible, a model-independent feedback control loop is employed, which can accomplish further reduction of the residual vibration of flexible appendages. This proposed control strategy is practical as it does not require direct measurement of mode vibration, and also has a simple structure with low online computational load. Numerical simulations demonstrate the effectiveness of the control strategy.

Keywords

active vibration suppression attitude manoeuvre feed-forward/feedback control flexible spacecraft

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