Proportional–integral–derivative attitude control subject to dynamic rate saturation of elevator through explicit command reshaping: An engineering approach

Abstract

In this article, an explicit pitch command governor for a kind of proportional–integral–derivative attitude control system is proposed based on the model predictive control philosophy to avoid the dynamic rate saturation in the elevator. In this command governor, the control horizon of the model predictive controller is selected as 1 such that the predicted saturations can be represented by a set of linear inequalities, which can significantly reduce the computational complexity, and the optimal solution can be calculated in real-time. The effectiveness of the proposed method is validated via numerical simulations. In addition, the limitations of this pitch governor are also revealed through investigating its scope of application in terms of uncertainties, nonlinearities and coupling effects.

Smooth backstepping sliding mode control for missile attitude system based on parameters online adjusting and estimating for square of disturbance upper bound

“…[1][2][3] A variety of nonlinear control schemes has been utilized in this field. [3][4][5][6] In Luo et al, 7 one adaptive control law based on inverse optimal strategy is proposed in order to solve the attitude tracking problem for a class of rigid space craft with uncertain inertia matrices and unknown external disturbances, which achieved the asymptotic attitude tracking in the presence of bounded equivalent disturbances. In Song et al, 3 the uniformly and globally stable of closedloop missile attitude control system with matching uncertainties is guaranteed, by employing quaternion feedback control law and vector thrust technique.…”