摘要: Different techniques of attitude and vibration control were applied to structural dynamic models, representative of large flexible spacecraft. The high order systems are reduced to tractable design models using different order red... 展开 Different techniques of attitude and vibration control were applied to structural dynamic models, representative of large flexible spacecraft. The high order systems are reduced to tractable design models using different order reduction methods. A two staged controller design was applied, including sensor/actuator positioning, low authority control for structural damping augmentation, and superimposed high authority control. Fundamental problems to be studied in a laboratory experiment were derived. A test structure represented by a rectangular flexible plate suspended by wires is proposed. The test procedure envisaged includes an ideal approach with respect to the peripheral hardware, and a realistic test where specific performance limitations can be included. 收起