The attitude tracking control problem of uncertain rigid spacecraft without angular velocity measurements is addressed in this paper. The adaptive control law, which incorporates a velocity-generating filter from attitude measurements, is shown to ensure the asymptotic convergence of the attitude and angular velocity tracking errors despite unknown spacecraft inertia. Simulation results are presented to illustrate the theoretical results.
- Adaptive control
- Attitude tracking
- Output feedback
ASJC Scopus subject areas
- Control and Systems Engineering
- Electrical and Electronic Engineering