Abstract:

From an attitude control point of view, spacecrafts with moving flexible appendages are much more complex than those with fixed ones. Focusing on this sort of complex spacecraft, the attitude dynamics model is discussed and analyzed briefly in this paper, and then the uniform bounded stability of the output feedback based PD control system is proved theoretically. In order to guarantee the asymptotic stability of the system, an internal model based control system is constructed, and then the stability proof is given based on Lyapunov theory. With the model parameters published by the American geostationary meteorological satellite GOES 8, the two kinds of controllers are simulated and compared with each other. This paper draws the concluding remarks and proposes a possible research topic in the end.

Key words: Sun tracking solar array, Internal model principle, Flexible satellite, Attitude control