On the stability analysis of a discontinuous quaternion attitude control system

Septanto, Harry; Trilaksono, Bambang Riyanto; Syaichu-Rohman, Arief; Poetro, Ridanto Eko

doi:10.1109/icsengt.2012.6339363

Cited by 2 publications

(3 citation statements)

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“…Attitude control system plays an important role in these missions. Many research efforts on spacecraft attitude control design have been reported, that is, linear matrix inequality-(LMI-) based robust mixed 2 / ∞ attitude control system design with linearization of dynamics and kinematics approach [1]; LMI-based nonlinear continuous attitude control design, [2]; proportional-derivative+ (PD+) type output feedback attitude control system with uniformly practically asymptotically stability guarantee for its equilibrium points [3]; attitude control system with discontinuous control law applying inverse cotangent function [4]; and hybrid attitude control system with property of robustness to measurement noise [5], to name a few.…”

Section: Introductionmentioning

confidence: 99%

“…From an attitude determination calculation, orientation of spacecraft is obtained as a rotation matrix that belongs to special orthogonal order-3 space, SO (3). However, some parameterizations are usually employed in a design of attitude control that is also employed in [1][2][3][4][5]-all of them employ quaternion parameterization, except [1], which uses Euler angle parameterization.…”

Section: Introductionmentioning

confidence: 99%

“…There are many research results giving solution to this problem. They include discontinuous control approach [4], optimal control and finite time stability approach [8], backsteppingbased attitude control design [9], hybrid mechanism attitude control [5,10], and continuous nonlinear attitude control employing augmented dynamic [11], to name a few.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Quaternion-Based Attitude Control System Design of Single and Cooperative Spacecrafts: Boundedness of Solution Approach

Septanto

Trilaksono

Syaichu-Rohman

et al. 2014

Modelling and Simulation in Engineering

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It is well known that single equilibrium orientation point in matrix rotation is represented by two equilibrium points in quaternion. This fact would imply nonefficient control effort as well as problem in guaranteeing stability of the two equilibrium points in quaternion. This paper presents a solution to design quaternion-based spacecraft attitude control system whose saturation element is in its control law such that those problems are overcome. The proposed feature of methodology is the consideration on boundedness of solution in the control system design even in the presence of unknown external disturbance. The same methodology is also used to design cooperative spacecrafts attitude control system. Through the proposed method, the most relaxed information-state topology requirement is obtained, that is, the directed graph that contains a directed spanning tree. Some numerical simulations demonstrate effectiveness of the proposed feature of methodology.

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