Adaptive Attitude Control of Spacecraft Orbiting Around Asteroids
AIAA Scitech 2019 Forum
American Institute of Aeronautics and Astronautics
San Diego, CA
The development of an adaptive control system for the attitude control of spacecraft orbiting around rotating asteroids is the subject of this paper. It is assumed that inertia parameters of spacecraft, and zonal and sectorial harmonic coefficients associated with the gravitational field of asteroid are not known. The objective is to control the pitch, roll, and yaw trajectories. Based on linear time-varying model of the attitude dynamics of the spacecraft, an adaptive state variable feedback control law is derived. By Lyapunov analysis, it is shown that in the closed-loop system, the pitch, roll, and yaw angle trajectory tracking errors asymptotically converge to zero. For the purpose of the illustration, attitude control of spacecraft around Eros asteroid is considered. Simulated responses show that the adaptive law is effective in tracking the reference attitude angle trajectories despite uncertainties in the attitude dynamics, and random disturbance inputs.
Aerospace Engineering | Controls and Control Theory
Lee, K. W.,
Singh, S. N.
Adaptive Attitude Control of Spacecraft Orbiting Around Asteroids.
AIAA Scitech 2019 Forum, 2019
San Diego, CA: American Institute of Aeronautics and Astronautics.