Two-body space dynamics technology demonstration for the biceps small satellite mission
Abstract
The recently proposed Canadian BICEPS mission requires co-orbiting two small satellites that allow for scientific experiments to be performed at a range of separation distances. Two implementation options have been identified: the preferred approach is to tether the two subsatellites and spin them in a cartwheeling manner to maintain tension in the tether; and the other is to use two free-flying small satellites with reaction control capability on one satellite so that it can be maneuvered relative to the other. One of the scientific objectives of the BICEPS mission is to study the dynamics of this two-body configuration. This paper primarily describes the proposed dynamics-related research activities associated with the tethered configuration, and a brief research summary is provided for the free-flying configuration. The deployment strategy of the tethered configuration is also described and a preliminary dynamics analysis is presented. It is shown that a cold-gas propulsion system is needed on at least one subsatellite to spin-up the system at several stages during the tether deployment in order to maintain tether tensions below 2250 N (approximately 500 lb). Generally, it is believed that the BICEPS mission offers possibilities for technology advancement of co-orbiting small satellites, and in particular tethered small satellites - and in so doing would develop a Canadian niche technology area.
- Publication:
-
Canadian Aeronautics and Space Journal
- Pub Date:
- March 1994
- Bibcode:
- 1994CaASJ..40....3T
- Keywords:
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- Flight Mechanics;
- Small Scientific Satellites;
- Spacecraft Maneuvers;
- Spacecraft Propulsion;
- Tethered Satellites;
- Dynamic Models;
- Research;
- Satellite Rotation;
- Space Flight;
- Spacecraft Design, Testing and Performance