DUAL REACTION WHEEL CONTROL OF SPACECRAFT POINTING,
Abstract
A method of spacecraft pointing control by the use of two body-fixed reaction wheels is proposed, and the development of an appropriate set of control laws, design relationships, and a performance analysis of a sample design are presented. One reaction wheel, designated as primary, is to spin at a nominal, non-zero constant speed and, by itself, is a basis for a momentum bias or spin-despin type of attitude stabilization. A second wheel is mounted in the spacecraft so that its spin axis is perpendicular to that of the primary wheel. The inclusion of the second wheel and control of its speed enhances the spin-despin control system capabilities in two respects: (1) provision for precise attitude maneuverability, and (2) rapid damping of nutation. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1967
- Accession Number
- AD0664327
Entities
People
- Richard M. Terasaki
Organizations
- The Aerospace Corporation