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.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science