Sliding mode attitude controller design for hypersonic aircraft based on dynamic inverse method and control parameters self-tuning

Cheng Zhihao; Wang Peng

doi:10.1117/12.2682894

16 June 2023 Sliding mode attitude controller design for hypersonic aircraft based on dynamic inverse method and control parameters self-tuning

Cheng Zhihao, Wang Peng

Author Affiliations +

Proceedings Volume 12703, Sixth International Conference on Intelligent Computing, Communication, and Devices (ICCD 2023); 127032O (2023) https://doi.org/10.1117/12.2682894
Event: Sixth International Conference on Intelligent Computing, Communication, and Devices (ICCD 2023), 2023, Hong Kong, China

Abstract

In order to study the sliding mode control method of hypersonic aircraft, the six-degree-of-freedom attitude motion model of hypersonic aircraft was established, and the corresponding linearization and decoupling model was obtained by using dynamic inverse method. On this basis, a sliding mode controller based on exponential approach rate is designed, and the controller is reconstructed by introducing the method of instruction parameterization, which greatly reduces the workload of control parameter tuning. In the end, Continuous Action Reinforcement Learning Automata (CARLA) is improved to optimize the new control parameters. Simulation shows that the algorithm can tune out a set of high-quality control parameters in 100 iterations, enabling the control system to quickly and accurately track a given instruction.

Citation Download Citation

Cheng Zhihao and Wang Peng "Sliding mode attitude controller design for hypersonic aircraft based on dynamic inverse method and control parameters self-tuning", Proc. SPIE 12703, Sixth International Conference on Intelligent Computing, Communication, and Devices (ICCD 2023), 127032O (16 June 2023); https://doi.org/10.1117/12.2682894

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