Affiliation:
1. College of Automation Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
2. College of Electronic Information and Automation Engineering, Guilin University of Aerospace Technology, Guilin 541004, China
Abstract
In order to obtain good flight performance in the near-space morphing vehicle (NMV) cruise phase, this paper proposes an adaptive sliding mode backstepping control scheme based on a neural network, aiming at the reduction of elevator control efficiency and issues of uncertainties. Firstly, this paper analyzes the aerodynamic parameters of NMV in the states of winglet stretching and retracting during the cruise phase. Based on the above, the flight efficiency of NMV can be improved by retracting winglets in the level flight mode and stretching winglets in the altitude climbing mode. Secondly, an enhanced triple power reaching law (ETPRL) is proposed to ensure that the sliding mode control system can converge quickly and reduce chattering. Then, the sliding mode control based on ETPRL and backstepping control are combined to ensure the stability of the system, and adaptive control laws are developed to estimate and compensate for uncertainties. In addition, in face of the problem of reduced elevator control efficiency, the adaptive neural network is used to estimate and compensate for interference on the control channel to improve tracking accuracy and robustness of NMV. Finally, three sets of simulations verified the effectiveness of the proposed method.
Reference33 articles.
1. A review of design issues specific to hypersonic flight vehicles;Sziroczak;Prog. Aerosp. Sci.,2016
2. Adaptive mode switching of hypersonic morphing aircraft based on type-2 TSK fuzzy sliding mode control;Jiao;Sci. China Inform. Sci.,2015
3. Adaptive control for hypersonic vehicles with time-varying faults;Hu;IEEE Trans. Aerosp. Electron. Syst.,2018
4. Zhao, K., Song, J., Ai, S., Xu, X., and Liu, Y. (2022). Active Fault-Tolerant Control for Near-Space Hypersonic Vehicles. Aerospace, 9.
5. Dong, M., Xu, X., and Xie, F. (2022). Constrained Integrated Guidance and Control Scheme for Strap-Down Hypersonic Flight Vehicles with Partial Measurement and Unmatched Uncertainties. Aerospace, 9.
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