自动化学报2023，Vol.49Issue(12)：2532-2543,12.DOI:10.16383/j.aas.c210646
基于ACP理论的微型扑翼飞行器的姿态控制
Attitude Control for Flapping Wing Micro Aerial Vehicle Based on ACP Theory
摘要
Abstract
Flapping wing micro aerial vehicle(FWMAV)plays an important role in the research and application of aircraft,due to its significant advantages,such as high flight efficiency,low weight,low energy conservation,high flexibility and so on.Currently,the attitude trajectory tracking control of FWMAV has become a research hotspot in the field of aircraft control.To this end,an anti-disturbance controller based on parallel intelligence theory is proposed in this paper.Specifically,via the construction of artificial systems(A),computational experiments(C),and parallel execution(P),the proposed controller can effectively address the disturbance issue in FWMAV atti-tude tracking.Moreover,the effectiveness and feasibility of the proposed controller are proved by theoretical ana-lyses and numerical simulations.关键词
微型扑翼飞行器/姿态控制/神经动力学/平行智能Key words
Flapping wing micro aerial vehicle(FWMAV)/attitude trajectory tracking control/neural dynamics(ND)/parallel intelligence引用本文复制引用
金龙,李嘉昌,常振强,卢经纬,程龙..基于ACP理论的微型扑翼飞行器的姿态控制[J].自动化学报,2023,49(12):2532-2543,12.基金项目
国家自然科学基金(62176109),甘肃省自然科学基金(21JR7RA 531,22JR5RA487),中央高校基本科研业务费项目(lzujbky-2023-ct05,lzujbky-2023-ey07),兰州大学超级计算中心资助Supported by National Natural Science Foundation of China(62176109),Natural Science Foundation of Gansu Province(21JR7RA531,22JR5RA487),Fundamental Research Funds for the Central Universities(lzujbky-2023-ct05,lzujbky-2023-ey07),and Supercomputing Center of Lanzhou University （62176109）
