The investigation of 3 Dimensional Reaction Wheel
- Paper number
IAC-06-B5.6.10
- Author
Mr. Atsushi Iwakura, University of Toukai, Japan
- Coauthor
Dr. Yuichi Tsuda, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2006
- Abstract
This paper presents a novel attitude control device called 3 Dimensional Reaction Wheel (3DRW). 3DRW consists of a spherical mass, which can rotate around arbitrary axes by magnetic levitation. 3DRW is 3-DOF device with only one reaction mass, which could make it possible to drastically reduce the weight and volume of the system as compared to existing reaction wheel. In addition to that, this device does not have mechanical contact between rotor and stator, so longer operating lifetime can be expected. The advantage of 3DRW is emphasized when used as the zero-momentum attitude control system of small satellite. It can be said with no doubt that the future space mission requires longer lifetime with more highly-integrated spacecraft systems. Especially recent small satellite missions impose sophisticated mission requirements for its weight and volume resources. 3DRW achieves 3 axes attitude control is just one component. Consequently it is possible to constitute lighter weight control device with the accuracy almost the same as conventional reaction wheel. The key technology of 3DRW is the metal ball fixed the constant position by magnetic levitation, and the rotational torque can be applied around arbitrary axes by Lorentz force. This Lorentz force is generated by the interaction between rotating magnetic field and eddy current. Although the magnetic levitation is originally instable, it is stabilized by a feedback controller. Some key and basic characteristics are examined and confirmed both by numerical simulation and magnetic levitation experiment. In the presentation, the design of 3DRW is introduced, and the analysis and numerical simulation results of magnetic field and rotation mass dynamics are shown. Also the experiment setup of magnetic levitation and rotating, and its result are presented. Finally we will mention how 3DRW system can be applied effectively for the small satellites.
- Abstract document
- Manuscript document
IAC-06-B5.6.10.pdf (🔒 authorized access only).
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