[1]秦 勇,祖家奎,位士超.倾转旋翼机直升机模式抗风控制律设计[J].机械与电子,2026,44(04):98-107.
　QIN Yong,ZU Jiakui,WEI Shichao.Design of Wind Resistance Control Law for Tiltrotor in Helicopter Flight Mode[J].Machinery & Electronics,2026,44(04):98-107.
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倾转旋翼机直升机模式抗风控制律设计()
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《机械与电子》[ISSN:1001-2257/CN:52-1052/TH]

卷:
44
期数:
2026年04期
页码:
98-107
栏目:
飞行控制与导航
出版日期:
2026-04-27

文章信息/Info

Title:
Design of Wind Resistance Control Law for Tiltrotor in Helicopter Flight Mode
文章编号:
1001-2257 ( 2026 ) 04-0098-08
作者:
秦 勇; 祖家奎; 位士超
南京航空航天大学自动化学院,江苏 南京 211106
Author(s):
QIN Yong ;  ZU Jiakui ;  WEI Shichao
( College of Automation Engineering , Nanjing University of Aeronautics and Astronautics , Nanjing 211106 , China )
关键词:
倾转旋翼机; 直升机模式; 风扰动; 操纵冗余; 非线性自抗扰
Keywords:
tiltrotor aircraft ;  helicopter mode ;  wind disturbance ;  control redundancy ;  nonlinear active disturbance rejection control ( NADRC )
分类号:
V249.1
文献标志码:
A
摘要:
针对倾转旋翼机在直升机模式垂直起降及悬停/小速度段易受风扰动,导致位置偏移、滚转角震荡威胁飞行安全的问题,以 XV-15 倾转旋翼机为研究对象,开展抗风控制律研究。分析倾转旋翼机直升机模式下风扰动的动力学作用机理,指出常规横向通道控制律存在姿态震荡、内环和外环耦合的局限性。由此,提出了一种改进的抗风控制方法:即通过横向周期变距控制横向外环速度/位置,差动总距控制内环横滚角及横滚角速率,并在内环姿态控制中引入自抗扰控制器。为验证该控制方法有效性,设计风扰动场景下自抗扰控制器与常规 PID 控制器的横滚角控制效果对比试验,基于 MATLAB / Simulink 与 X-Plane搭建联合仿真验证平台,将常规控制律与改进控制律在风扰下的动态响应进行对比分析。仿真结果表明,所提出的控制律能显著提升系统在侧风扰动下的稳定性、鲁棒性及动态跟踪性能,从而为倾转旋翼机直升机模式抗风控制律设计提供了理论与方法支撑。
Abstract:
Tiltrotor aircraft during vertical take off and landing , hover , or low speed flight in helicopter flight mode are susceptible to wind disturbances , which can induce position drift and roll oscillations , thereby threatening flight safety.Addressing this issue , this paper investigates a wind resistant control law for the XV-15 tiltrotor.The dynamic mechanism of crosswind disturbance on tiltrotor aircraft in helicopter mode is analyzed , highlighting the limitations of conventional lateral control laws , including attitude oscillations and the coupling between the inner and outer control loops.Consequently , an improved wind resistant control method is proposed , i.e.the lateral cyclic pitch is employed to control the lateral velocity / position in the outer loop , while differential collective pitch is used to regulate the roll angle and roll rate in the inner loop.Furthermore , a nonlinear active disturbance rejection controller ( NADRC ) is introduced into the inner loop attitude control.To verify the effectiveness of the proposed method , a comparative study of roll angle control performance under wind disturbance scenarios is designed , contrasting the ADRC with a conventional PID controller.A co-simulation platform based on MATLAB / Simulink and X-Plane is established to compare and analyze the dynamic responses of the conventional control law and the improved control law under wind disturbances.Simulation results demonstrate that the proposed control strategy significantly enhances system stability , robustness , and dynamic tracking performance under lateral wind disturbances , thereby providing theoretical and methodological support for the design of wind-resistant control laws for tiltrotor aircraft in helicopter mode.

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期: 2025-08-28
作者简介:秦 勇 ( 1999- ),男,安徽合肥人,硕士研究生,研究方向为飞行控制、嵌入式系统;祖家奎 ( 1974- ),男,江苏徐州人,博士,副研究员,研究方向为飞行控制、嵌入式系统。
更新日期/Last Update: 2026-08-21