Slewing Flexible Spacecraft with Deflection-Limiting Input Shaping

Abstract

A control scheme is described for slewing è exible spacecraft with both suppression of deè ection during the slew and elimination of residual oscillations. The method minimizes the maneuver time subject to constraints on residual vibration magnitude, sensitivity to modeling errors, rest-to-rest slew distance, and the transient deè ection amplitude. Furthermore, a solution is sought that provides inherent fuel efé ciency. The feasibility of the approach is demonstrated with linear and nonlinear computer simulations.