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Second Order Sliding Mode-Based Output Feedback Tracking Control of Spacecraft Attitude Tracking

Chutiphon Pukdeboon

Abstract



This paper investigates an output feedback attitude tracking control problem for rigid space-craft when uncertainties related to system parameters and external disturbances are taken into account. A new finite-time attitude control law using adaptive second order sliding mode control approach is developed to solve this problem. This controller has an adaptive tuning law to relax the requirement of prior knowledge about the upper bound of the system uncertainties. The finite-time stability of the closed-loop system is ensured by the Lyapunov stability theory. In addition, we introduce an adaptive sliding mode differentiator to estimate the time derivative of attitude so that angular velocity measurements are not required. Numerical simulations of and attitude control of spacecraft are given to illustrate effectiveness of the proposed controller.

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