南京航空航天大学学报（自然科学版）2026，Vol.58Issue(2)：331-338,8.DOI:10.16356/j.2097-6771.2026.02.009
倾转旋翼机纵向一体化姿态控制律设计及鲁棒性分析
Longitudinal Integrated Attitude Control Law Design and Robustness Analysis of Tiltrotor Aircraft
陈国军 1刘毅 1张威1
作者信息
- 1. 中国直升机设计研究所,景德镇 333001
- 折叠
摘要
Abstract
Since the tiltrotor aircraft needs to switch configurations among helicopter mode,transition mode,and fixed-wing mode within its flight envelope,and its dynamic characteristics vary significantly under different configurations,it is necessary to design control laws for different configurations to ensure satisfactory control performance across all three modes.To address this issue,a six-degree-of-freedom nonlinear model of the tiltrotor aircraft considering center-of-mass movement is established.An integrated control law with a unified structure is designed,and normalized weighting coefficients are introduced for the transition mode.Taking the longitudinal control channel as an example,mathematical simulation results show that the designed integrated control law achieves satisfactory control accuracy in all three modes and demonstrates good robustness under both model uncertainties and control law parameter variations.关键词
倾转旋翼机/质心移动建模/飞行控制/一体化设计/鲁棒性分析Key words
tiltrotor aircraft/center-of-mass movement modeling/flight control/integrated design/robust analysis分类
航空航天引用本文复制引用
陈国军,刘毅,张威..倾转旋翼机纵向一体化姿态控制律设计及鲁棒性分析[J].南京航空航天大学学报（自然科学版）,2026,58(2):331-338,8.
