Study on the Investigation of the Attitude Control of Large Flexible Spacecraft. Phase 2, Volume 2: Technical Report

摘要

The hardware, experimental and theoretical modeling of the test element, and development and implementation of the controller software for large flexible spacecraft model simulation are described. Based on a finite element method structural model, confirmed by the experimental results, different sensor and actuator positions are derived. For selected configurations, active vibration and attitude controller design is performed. The feasibility of the approaches is proved by a computer performance simulation. The implementation of control laws is realized by an array processor real time routine. The experiments to be performed are summarized.