Abstract
A margin of safety for a multi-thruster system is defined, by normalizing the thruster configuration matrix by the worst disturbance environment. The margin of safety is maximized to yield an optimal thruster configuration. Two thruster controllers are presented for one-sided thruster systems. A nonlinear pseudoinverse controller based on a modified Newton Raphson iteration is shown to have higher control authority than one based on a biased pseudoinverse controller. These controllers, as well as the thruster configuration optimization technique, are applied to the design of a thruster system for the Quick STEP (Quick Satellite Test of Equivalence Principle) spacecraft.
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