Principal axis misalignment control for deconing of spinning spacecraft
Deconing controllers are developed for a spinning spacecraft, where the control mechanism is that of axial or radial moving masses that are used to produce intentional, transient principal axis misalignments. A single mass axial controller issued to motivate the concept, and then axial and radial dual mass controllers are described. The two mass problem is of particular interest since spacecraft imbalances can be simultaneously removed with the same control logic. Each controller is tested via simulation for its ability to eliminate existing coning motion for a range of spin rates. Both controllers are developed via a linear-quadratic-regulator synthesis procedure, which is motivated by their multi-input/multi-output nature. The dynamic coupling in the radial two mass control problem introduces some particularly interesting design complications. 10 refs.
- Research Organization:
- Sandia National Labs., Albuquerque, NM (United States)
- Sponsoring Organization:
- USDOE, Washington, DC (United States)
- DOE Contract Number:
- AC04-76DP00789
- OSTI ID:
- 10117807
- Report Number(s):
- SAND-91-2823C; CONF-920845-1-Draft; ON: DE92006802
- Resource Relation:
- Conference: American Institute of Aeronautics and Astronautics (AIAA) meeting,Hilton Head, SC (United States),10-12 Aug 1992; Other Information: PBD: [1992]
- Country of Publication:
- United States
- Language:
- English
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