Abstract
A new formulation of independent modal space control is developed to handle the attitude and shape control problem for large flexible spacecraft. The main advantage of this method is that one can obtain an analytical solution for the optimal control law for very high dimensional systems. The fundamental limitation of previous work—the requirement of one actuator for each mode to be controlled—is relaxed in the new formulation. The closed-loop design is obtained while independently assuring stability and the design may be iterated to improve closed-loop performance. The process is shown to be simple and efficient in a realistic numerical example of spacecraft shape and attitude control. The ease of control law generation by this approach is seen to be obtained at the expense of the ability to adjust directly the penalties on the actuator effort. Actuator placement is seen to be of fundamental importance, and methods are developed which are comparatively simple to use and which can determine optimal actuator locations.
Published Version
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