Attitude Stability Technique in a Micro Satellite Model Using Eventual Sliding Mode Controller

Abstract

The feasibility study has been investigated to build a small satellite (so called `nano-satellite'), which has 3-kg mass and less than 30-W power, since October in 1998. The experimental 3-axes attitude control of the nano-satellite under micro-gravity field is conducted at in Japan Micro-gravity Center ( JAMIC) in 2002. The small reaction wheel is used as an actuator for the attitude control and enables compensate the small residual deviation of the presume error. This project investigates the validity of the feedback control with the eventual sliding mode control because of the correspondence for the non-linearity of the control system and the excellence for robustness.