Adaptive Control for Spacecraft Rendezvous Subject to Time-Varying Inertial Parameters and Actuator Faults

Kewei Xia, Sang Young Park

Research output: Contribution to journalArticle

Abstract

A novel adaptive fault-tolerant control strategy is proposed for a spacecraft rendezvous maneuver. The six-degree-of-freedom (6-DOF) nonlinear model is expressed in the pursuer's body frame, which consists of relative attitude and orbit dynamics in the presence of unknown time-varying inertia parameters, bounded disturbances, and actuator faults. A continuous adaptive control strategy is developed for the pursuer where a modification term and projection algorithm are employed in the adaptation laws to ensure the estimates of the unknown parameters remain positive and bounded. It is proven that the proposed strategy ensures the ultimate boundedness of all the signals in the closed-loop system and the asymptotic stability of the relative dynamics. Numerical simulations verify the effectiveness of the proposed control strategy.

Original languageEnglish
Article number04019063
JournalJournal of Aerospace Engineering
Volume32
Issue number5
DOIs
Publication statusPublished - 2019 Sep 1

Fingerprint

Space rendezvous
Actuators
Asymptotic stability
Closed loop systems
Orbits
Computer simulation

All Science Journal Classification (ASJC) codes

  • Civil and Structural Engineering
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanical Engineering

Cite this

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abstract = "A novel adaptive fault-tolerant control strategy is proposed for a spacecraft rendezvous maneuver. The six-degree-of-freedom (6-DOF) nonlinear model is expressed in the pursuer's body frame, which consists of relative attitude and orbit dynamics in the presence of unknown time-varying inertia parameters, bounded disturbances, and actuator faults. A continuous adaptive control strategy is developed for the pursuer where a modification term and projection algorithm are employed in the adaptation laws to ensure the estimates of the unknown parameters remain positive and bounded. It is proven that the proposed strategy ensures the ultimate boundedness of all the signals in the closed-loop system and the asymptotic stability of the relative dynamics. Numerical simulations verify the effectiveness of the proposed control strategy.",
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Adaptive Control for Spacecraft Rendezvous Subject to Time-Varying Inertial Parameters and Actuator Faults. / Xia, Kewei; Park, Sang Young.

In: Journal of Aerospace Engineering, Vol. 32, No. 5, 04019063, 01.09.2019.

Research output: Contribution to journalArticle

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