General Considerations in the Selection of Attitude Control Systems Spacecraft Dept., General Electric Company

Format:

Conference/Event

Author/Creator:

Woestemeyer, F. B., author.

Conference Name:

NASA Aerospace Vehicle Flight Control Conference (1965-07-13 : Los Angeles, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1965

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

650591

Access Restriction:

Restricted for use by site license