Robust Finite-Time Control for Spacecraft with Coupled Translation and Attitude Dynamics

Abstract

Robust finite-time control for spacecraft with coupled translation and attitude dynamics is investigated in the paper. An error-based spacecraft motion model in six-degree-of-freedom is firstly developed. Then a finite-time controller based on nonsingular terminal sliding mode control technique is proposed to achieve translation and attitude maneuvers in the presence of model uncertainties and environmental perturbations. A finite-time observer is designed and a modified controller is then proposed to deal with uncertainties and perturbations and alleviate chattering. Numerical simulations are finally provided to illustrate the performance of the proposed controllers.

Robust optimal sliding mode control for spacecraft position and attitude maneuvers

“…al. [53]. Both controllers are defined using the smooth SOISMC controller (60) with u s defined in (63).…”

“…[8], [52], [53]). This model is sufficiently good that it can be used in this paper to design optimal position and attitude control for spacecraft.…”

“…This implies that ξ will approach to the region In the simulations, the parameters of controller (63) were set as β = 5 7 , λ = 0.8, μ 1i = 5.0, μ 2i = 2.0, μ 3i = 3.0 μ 4i = 1.0 (i = 1, · · · , 6) and The bounded disturbance forces and toques are assumed to be In view of these simulation results, the NTSM controller (20)in Wu et al [53] gives the worst tracking effect. In addition, this control takes high magnitudes of control torques and forces without considering the minimization of any cost functional.…”

Inverse optimal sliding mode control of spacecraft with coupled translation and attitude dynamics

“…In this section, the results of numerical simulations are presented to compare the performance of the proposed IOSMC law (58) and H ∞ inverse controller (93) with the gainscheduled minimum norm controller (17) in Horri, Palmer, and Roberts (2012) and the finite-time TSMC law (20) in Wu et al (2013). The model of the spacecraft used in the simulations is taken from Wu et al (2013), where the spacecraft parameters are given by …”

Free-flying dynamics and control of an astronaut assistant robot based on fuzzy sliding mode algorithm

“…So, many scholars have made a deep research on the position and attitude control of the in-cabin free-flight robot or the similar model such as spacecraft and small satellites. For example, Wu et al used robust finite-time algorithm to the spacecraft which has a coupled translation and attitude dynamics [8]; Wang and Liang used dual-quaternion-based finite-time control to study the spacecraft tracking in six degrees of freedom [9]; Li and Jing used 6-DOF optimal dynamic inversion control to investigate the active satellite tracking [10]; Lincoln and Veres designed a 6-DOF variable hierarchy sliding mode controller to the satellite in Halo orbits [11].…”