The flexure-satellite attitude interaction due to two uniform beam arrays on a three-axis stabilized spacecraft is examined. It is shown that flexure interaction with the reaction wheel roll and yaw axes causes instability. Improved control schemes which take flexure into account were therefore derived for the reaction wheel actuator system. Both classical and modern control techniques are employed resulting in the design of a compensation network and two observer-based multivariable feedback controllers. The result of a comparison of the three systems is that best control performance is given by an observer which is used to provide control signals for the rigid body mode, allowing the flexure mode to decay by structural damping. Methods of implementing in-flight experiment and data processing techniques to evaluate flexure parameters are compared.
The Attitude Control of Three-Axis Stabilised Spacecraft with Flexible Appendages, Volume 2, Book 2
1976
202 pages
Report
No indication
English