Abstract
This paper investigates the self-healing control problem for the large launch vehicle (LLV) with system uncertainties, external disturbances, and actuator faults. First, the attitude dynamics of the LLV are presented, and the control-oriented model subject to undesired malfunctions is structured. Second, a novel extended state observer (ESO) is designed to estimate the disturbances and fault informations, and the nonlinear gain functions with two different linear ranges are introduced to improve the estimation accuracy and reduce the effect of peaking value problem. Then, an integral terminal sliding mode fault tolerant control scheme is proposed for the attitude faulty system, which would stabilize the closed-loop system even existing the disturbances and actuator failures. Besides, utilizing the adaptive dynamic programming (ADP) technique, a supplementary control with actor-critic structure is employed to further improve the system tracking performance and provide the additional compensation control input according to the bias between the desired value and actual one. Finally, the effectiveness of the proposed method is verified by the simulation results.
Highlights
With the development of the deep space explorations, the large launch vehicles (LLVs) have received extensive attention in aerospace engineering in the past few decades [1]
2) Based on the estimated informations, an integral terminal sliding mode fault tolerant control scheme is designed for the attitude tracking system of LLV, and the finite time stability of the closed-loop system can be achieved in presence of disturbances and actuator malfunctions
MAIN RESULTS the self-healing control strategy for LLV is proposed to stable attitude tracking systems
Summary
With the development of the deep space explorations, the large launch vehicles (LLVs) have received extensive attention in aerospace engineering in the past few decades [1]. In [21], a fixed-time extended state observer is proposed to estimate the grid fin faults and system uncertainties for reusable launch vehicle, and an adaptive fault-tolerant control method is developed by the nonsingular fast terminal sliding mode technique, which could guarantee a good tracking performance. If there is a discrepancy between the actual value and reference signals, the proposed ADP arithmetic would produce a supplementary control input to improve the system performance Both fault tolerant control and ADP methods have made some achievements, the organic combination of two approaches requires further study. 2) Based on the estimated informations, an integral terminal sliding mode fault tolerant control scheme is designed for the attitude tracking system of LLV, and the finite time stability of the closed-loop system can be achieved in presence of disturbances and actuator malfunctions. Sat (·) and sgn(·) represent the standard saturation function and sign function, respectively
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