Abstract In this chapter, the finite-time attitude tracking control problem for rigid spacecraft with external disturbances and inertia uncertainties is addressed. First, a novel fast nonsingular terminal sliding mode surface (FNTSMS) without any constraint is designed, which not only avoids the singularity problem, but also contains the advantages of the nonsingular terminal sliding mode (NTSM) and the conventional sliding-mode together. Second, the proposed FNTSM control laws (FNTSMCLs) by employing FNTSMS associated with adaptation provide finite-time convergence, robustness, faster, higher control precision. The proposed FNTSMCLs in light of novel adaptive control architecture are continuous. Thus, they are chattering-free. Finally, simulation results are presented to illustrate effectiveness of the control strategies. In addition, digital simulations of satellite Hubble Space Telescope (HST) are presented to verify the practical feasibility of the reorientation/ slew maneuvers mission.
Adaptive Attitude Tracking Control for Rigid Spacecraft with Finite-Time Convergence
03.07.2018
19 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Adaptive Finite-Time Control for Attitude Tracking of Rigid Spacecraft
Online Contents | 2016
|Adaptive Finite-Time Control for Attitude Tracking of Rigid Spacecraft
Online Contents | 2016
|