Robust nonlinear H_∞ output-feedback control for flexible spacecraft attitude manoeuvring

Abstract

This paper presents a robust nonlinear H∞ output-feedback control approach for attitude manoeuvring of flexible spacecraft with external disturbances, inertia matrix perturbation and input constraints. By applying Lyapunov stability theory and using the generalized S-procedure and sum of squares (SOS) techniques, the robust H∞ output-feedback attitude control problem is converted into a convex optimization problem with SOS constraints when the flexible spacecraft is modelled as a polynomial state-space equation with polytope uncertainties. As a result, it overcomes the difficulty in constructing Lyapunov function and implementing numerical computation caused by the non-convexity of output-feedback H∞ control design for nonlinear systems. Moreover, it enables the state-observer and the controller to be designed independently and hence the complexity of the control algorithm is reduced remarkably. A numerical example illustrates the effectiveness and feasibility of the proposed approach.

Observer-based multi-objective parametric design for spacecraft with super flexible netted antennas

“…Problem MOD. For given system (3)-(9), find gain matrices K and L in the observer-based control law (10), such that (1) The poles of the closed-loop system (11), that is, the eigenvalues of A z , are assigned to the desired positions or regions, and are as insensitive as possible to parameter perturbations ∆a 1 and ∆a 2 ;…”

“…For example, in 1958 the satellite named "Explorer-1" caused the energy dissipation in the system owing to the flexible vibration of the four whip antennas that eventually led to the attitude roll [1]. Therefore, vibration suppression and attitude control of spacecraft with large flexible attachments is a critical problem and it has received lots of attention [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21]. Sliding mode control (SMC) and backstepping control are commonly used control methods in order to solve this problem.…”

“…problem of a flexible spacecraft in the presence of disturbances, parameter uncertainties and actuator saturation based on LMI approach. The problems of robust H ∞ controller design with input constraints are considered in [11,12]. In addition to SMC, backstepping, and robust H ∞ control, many other control methods are also applied to the vibration suppression and attitude control of flexible satellites, such as disturbance observer-based control [13][14][15], adaptive control [16][17][18][19][20], and finite-time control [16,18,21].…”

“…In addition to SMC, backstepping, and robust H ∞ control, many other control methods are also applied to the vibration suppression and attitude control of flexible satellites, such as disturbance observer-based control [13][14][15], adaptive control [16][17][18][19][20], and finite-time control [16,18,21]. Many of the current control methods are proposed for a single control target (e.g., [2][3][4][5][6][7][8][11][12][13][14][15][16][17][18][19][20][21]) to provide flexible spacecraft control. However, in actual engineering, we need to consider the accuracy, rapidity, smoothness, the influences of parameter perturbations, and high-order unmodeled dynamics at the same time.…”

Adaptive fault tolerant attitude control of flexible satellites based on Takagi-Sugeno fuzzy disturbance modeling

“…When a satellite contains flexible appendages, the problem of attitude control becomes more complicated. Anti-disturbance PD control (Liu and Guo, 2012), robust H ∞ output feedback (Bai et al, 2019), nonlinear control based on an estimator (Xiao et al, 2017), sliding mode observer based control (Zhang et al, 2016b) were addressed to the problem of ACS for flexible spacecrafts.…”