General Considerations in the Selection of Attitude Control Systems 650591
To the great benefit of the Spacecraft designer, there is now a broad spectrum of Guidance and Control techniques and components from which to choose. Thus, in the integration of the overall vehicle, he has considerable freedom in selecting not only the preferred components but also the most advantageous modes of system operation. Guidance and control functions are usually interrelated, and the optimum choice may have a major effect on the vehicle contiguration. This paper considers the constraints affecting the choice of the basic Attitude Control system to be used and tradeoffs in the selection, sizing, and mode of operation of the components with which it may be implemented. The primary characteristics, both of the techniques and the hardware, are classified according to various criteria. The spectrum of vehicles is also classified according to characteristic requirements. Examples are drawn from existing spacecraft. Other systems now awaiting suitable application, or under development, are discussed and characteristic advantages defined.