Abstract:
A solution to the problem of tracking a desired attitude of spacecraft under the parameter uncertainty using contraction analysis is given in this paper. First, an ideal ...View moreMetadata
Abstract:
A solution to the problem of tracking a desired attitude of spacecraft under the parameter uncertainty using contraction analysis is given in this paper. First, an ideal state feedback controller, assuming the knowledge of the inertial matrix and the total angular momentum, is devised and ensured to be contracting. Then the adaptive control law is designed in a certainty equivalence fashion substituting the controller parameter vector by its estimate. The overall system is shown to be contracting under a sufficient excitation condition, which is strictly weaker than the persistent excitation required for most adaptive control schemes.
Date of Conference: 12-15 December 2017
Date Added to IEEE Xplore: 22 January 2018
ISBN Information: