Attitude Control of Large Flexible Spacecraft,
Abstract
This paper presents some results found during the investigation of control problems of large flexible spacecraft*. A triple plate configuration of such a spacecraft is defined and studied. The model is defined by modal data derived from finite element modelling. The order reduction methods applied are briefly described and results of order reduction are presented. An attitude control concept with low and high authority control has been used to design an attitude controller for the reduced model. The stability and response of the original system together with the reduced controller is analysed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1984
- Accession Number
- ADP003395
Entities
People
- G. Thieme