Attractive Manifold-Based Adaptive Solar Attitude Control of Satellites in Elliptic Orbits

Document Type

Article

Publication Date

8-3-2010

Publication Title

Acta Astronautica

Volume

68

Issue

1-2

First page number:

185

Last page number:

196

Abstract

The paper presents a novel noncertainty-equivalent adaptive (NCEA) control system for the pitch attitude control of satellites in elliptic orbits using solar radiation pressure (SRP). The satellite is equipped with two identical solar flaps to produce control moments. The adaptive law is based on the attractive manifold design using filtered signals for synthesis, which is a modification of the immersion and invariance (I&I) method. The control system has a modular controller–estimator structure and has separate tunable gains. A special feature of this NCEA law is that the trajectories of the satellite converge to a manifold in an extended state space, and the adaptive law recovers the performance of a deterministic controller. This recovery of performance cannot be obtained with certainty-equivalent adaptive (CEA) laws. Simulation results are presented which show that the NCEA law accomplishes precise attitude control of the satellite in an elliptic orbit, despite large parameter uncertainties.

Keywords

Adaptive control systems; Adaptive satellite attitude control; Artificial satellites—Attitude control systems; Attitude control in elliptic orbits; Elliptical orbits; Nonlinear adaptive control; Parameter estimation; Solar radiation pressure

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