Switching disturbance rejection attitude control of near space vehicles with variable structure

Abstract

A switching disturbance rejection attitude control law is proposed for a near space vehicle (NSV) with variable structure. The multiple flight modes, system uncertainties and disturbances of the NSV are taken into account based on switched nonlinear systems. Compared with traditional backstepping design methods, the proposed method utilizes the added integrals of attitude angle and angular rate tracking errors to further decrease the tracking errors. Moreover, to reduce the computation complexity, a rapid convergent differentiator is employed to obtain the derivative of the virtual control command. Finally, for disturbance rejection, based on the idea from the extended state observer (ESO), two disturbance observers are designed by using non-smooth functions to estimate the disturbances in the switched nonlinear systems. All signals of the closed-loop system are proven to be uniformly ultimately bounded under the Lyapunov function framework. Simulation results demonstrate the effectiveness of the proposed control scheme.

Back-stepping Active Disturbance Rejection Control for Attitude Control of Aircraft Systems Based on Extended State Observer

“…Remark 1: The introduction of H(t) is based on strict mathematical logic. In (14), (7) and system (8) shows that H(t) is derivable. Furthermore, please refer to Table 1 in the text for the aerodynamic derivative in the aircraft system.…”

“…Attitude control system is no exception, and its nonlinear dynamics must also be considered [2]. Various nonlinear control algorithms, such as fault tolerant control [3][4][5], that studied H ∞ fault tolerant attitude control of satellite with actuator and sensor faults based on observer; fuzzy adaptive algorithm [6,7]; variable structure control [8]; and sliding control [9,10], that studied the fixed time integral sliding mode control for the attitude stability of the quadrotor unmanned aerial vehicle with actuator failure; etc., have been proposed for solving the attitude control problem for spacecraft. However, so far, few scholars have studied the attitude control of aircraft by using ADRC; it is rare to study this problem in combination with the back-stepping method.…”

“…, is the main problem in system (8). The moment coefficients rely on the Mach number M a , which is also a variable related to the states…”