Integrated control method for spacecraft considering the flexibility of the spacecraft bus

This paper presents an integrated control method for an extremely large spacecraft, such as the space interferometry telescope, to achieve control task with high accuracy and high stability. The flexibility of the spacecraft bus would be more obvious when their size gets larger, so the vibration reduction for this kind of spacecraft would be more challenging. This paper presented a dynamic model of the spacecraft with flexible central body, and with flexible appendages and CMG (Control Moment Gyroscope) with disturbances at the same time. Then the integrated control method is presented to make the relative attitude of the two payloads on the spacecraft bus track with each other. The vibration isolation techniques are adopted to reduce the high frequency vibrations, and the nonlinear feedback control is presented to achieve the relative attitude convergence to 0 with high accuracy and high stability. Finally numerical simulations are carried out to verify the performance of the integrated control method.