Minimum energy control law for satellite reorientation by two wheels.
- Paper number
IAC-05-C1.P.13
- Author
Dr. Tatsuya Endo, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2005
- Abstract
This paper discusses on the optimal controller of small satellites that are required large angle maneuver with two reaction wheels. In the case of wheel malfunction, the control system of satellite with no redundant system is required to control the attitude on three axes by only two reaction wheels. The most difficult problem is control around the axis that has no available reaction wheel. The maneuver should be performed as less energy as possible. It is, however, impossible for small satellite to calculate the minimum energy trajectory by the on-board computer. The anthers provided a simple optimal algorithm for open loop controller that performs the reorientation on the no wheel axis by two wheels on the other axes. The proposed controller satisfies the required maneuver with a little additional energy consumption. Also, the anthers provide some optimal attitude trajectory of reorientation numerically. In some large angle maneuver, the trajectories of the attitude parameter are same figure like 'tear drop', and the trajectories of the inputs are the type ‘W’ figures. In this paper some simple impulsive inputs trajectory that is according to optimal attitude trajectory is discussed. And simple minimum energy control law of two reaction wheels, is applicable in any attitude is provide.
- Abstract document