STABILITY ANALYSIS OF FLEXIBLE SPACECRAFT WITH PID CONTROLLER

Authors
  1. De Lafontaine, J.
Corporate Authors
Communications Research Centre, Ottawa ONT (CAN)
Abstract
The study presents a graphical method for the design and analysis of a flexible spacecraft controller. It can handle as many modes as desired, in constrained or unconstrained form; modal separability is not assumed and the method is exact when the spacecraft axes are uncoupled. The definition of a "system function", independent of the controller parameters, simplifies the determination of the system stability boundaries. It also allows the investigation of the modal separability assumption, resulting in a criterion for its validity. Stabilization through structural damping and flexible modes filtering is illustrated using graphs of the system function. Closed-form approximations are derived in order to complement the exact, numerical method. Extensions to systems with loop delay and nonlinear elements are also included along with applications to the LSAT-1 Roll axis.
Report Number
1372 —
Date of publication
15 Nov 1984
Number of Pages
60
DSTKIM No
85-01261
CANDIS No
46079
Format(s):
Hardcopy;Originator's fiche received by DSIS

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