Continuous robust fault‐tolerant control and vibration suppression for flexible spacecraft without angular velocity

Abstract

Summary The fault‐tolerant control and vibration suppression for flexible spacecraft without angular velocity measurement are investigated. External disturbances, actuator faults, unknown angular velocity, and flexible vibration are addressed simultaneously. Firstly, a model‐free adaptive supertwisting state observer and an angular velocity calculation algorithm in one step are developed by using attitude information only, which can estimate the angular velocity in finite time. Then, on the basis of angular velocity estimation, a novel continuous multivariable integral sliding mode (CMISM) is proposed for the first time, which is a combination of continuous nominal controller and a modified multivariable twisting controller to reject disturbances and faults. The CMISM can stabilize attitudes in finite time and attenuate chattering effectively. Furthermore, the input shaping technique is developed to achieve effective vibration suppression of the flexible appendages. Finally, the efficiency of the proposed method is illustrated by numerical simulations.

Multi-Objective Non-Fragile Robust Attitude Control for Flexible Microsatellite Close-Proximity Inspection

“…Compared with the results in Figs. 8 and 9, we can observe that the proposed non-fragile RDOFC (8) guarantees that the Euler angles converge into a smaller convergent region than the robust controller in [39]. It is illustrated that the proposed non-fragile RDOFC (8) has better robustness performance and can achieve high control accuracy in the presence of the gain parameter perturbations.…”

“…(3) The control input u ≤ u max . We consider the closed-loop system (10) with the nonfragile RDOFC (8). With H ∞ performance index and the system control parameters as shown in Table 1, the associated matrices S > 0, N < 0, F a , F b , C f can be obtained by solving the LMIs ( 17), (19), (20).…”

Fuzzy Disturbance Observer-Based Sliding Mode Control for Liquid-Filled Spacecraft With Flexible Structure Under Control Saturation

“…The ε denotes approximation error of FLS, which is bounded byε. Substituting the (14) and 18into (17),ė can be rewritten asė = −σ e −θ T ξ + ε (19) whereθ =θ − θ * denotes the parameter estimation error. The e is exponentially convergent, whenθ approaches 0.…”

“…The associate editor coordinating the review of this manuscript and approving it for publication was Jianyong Yao . residence time and much more liquid fuel are needed for the spacecraft [16], [17]. However, due to the sloshing of the liquid fuel, the maneuverability of spacecraft is inevitably influenced, which causes the bad control performance and even the failure task [18], [19].…”

Finite‐time fault tolerant control for stochastic parameter systems with intermittent fault under stochastic communication protocol

“…Due mainly to the high‐demand on system reliability and security in a variety of industrial systems, fault detection, and fault tolerant control (FTC) issues have drawn much research attention in recent years, and tremendous research results have been documented, see, for example, References 1‐5. The main task of FTC is to recover the system with required performance when faults occur.…”