Thermally induced attitude disturbance control for spacecraft with a flexible boom

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17 Citations (Scopus)

Abstract

A spacecraft with a flexible appendage is analyzed by a coupled system composed of a flexible boom and a rigid main body, which is described by the finite element method (FEM). With constant attitude disturbances and vibrations, an active control system combines the integral control with the original PPF, by using an embedded piezoceramic device as actuators and sensors. This modified PPF technique achieves great control performance when the compensator is tuned to the modal frequency of the system. In addition, it provides good capability of controlling the main attitude disturbances from thermally induced structural deformations.

Original languageEnglish
Pages (from-to)325-328
Number of pages4
JournalJournal of Spacecraft and Rockets
Volume39
Issue number2
DOIs
Publication statusPublished - 2002

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

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