The Attitude Control Problem for Flexible Satellites General Dynamics/Convair

Format:

Conference/Event

Author/Creator:

Greensite, Arthur L., 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:

An attitude control system for a flexible satellite is investigated. It is assumed that the satellite can be analyzed, at least to a first approximation, as a thin circular plate. Certain types of orbiting telescopes fall in this category. The modes of vibration of this system are determined and their influence on the performance quality of a three axis control system is studied. Essential complications in the analysis stem from the non-linear gyroscopic coupling terms as well as the coupling of rigid body and elastic motion.It is shown that the elastic motions are reflected on only one axis of the vehicle with proper location of sensors, and that the control system can be made insensitive to the two lowest vibration modes. Furthermore, the inter axis coupling has negligible influence on the system stability if the control system for each axis is properly designed

Notes:

Vendor supplied data

Publisher Number:

650584

Access Restriction:

Restricted for use by site license