考虑飞行品质的倾转旋翼机LPV-PID控制设计方法

段登燕; 苏小恒; 严峰; 刘毅; 陈国军

doi:10.7527/S1000-6893.2026.33848

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DOI: https://doi.org/10.7527/S1000-6893.2026.33848

考虑飞行品质的倾转旋翼机LPV-PID控制设计方法

段登燕 ,
苏小恒 ,
严峰 ,
刘毅 ,
陈国军

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中国直升机设计研究所

收稿日期: 2026-05-08

修回日期: 2026-08-26

网络出版日期: 2026-09-02

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LPV-PID Control Design Method for Tiltrotor Aircraft Considering Flight Qualities

DUAN Deng-Yan ,
SU Xiao-Heng ,
YAN Feng ,
LIU Yi ,
CHEN Guo-Jun

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Received date: 2026-05-08

Revised date: 2026-08-26

Online published: 2026-09-02

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摘要

本文提出了一种考虑飞行品质的倾转旋翼机LPV-PID控制设计方法。针对倾转旋翼机，首先在飞行力学模型和倾转过渡走廊的基础上，线化得到了基于倾转角/前飞速度增益调度的线性变参数（LPV）模型。进而，基于模拟退火算法形成了考虑飞行品质的倾转旋翼机纵向通道控制参数优化设计方法，遍历得到了过渡走廊内不同飞行状态下的最优控制参数。进而，以LPV控制理论为基础，形成了基于倾转角/前飞速度增益调度的LPV-PID控制方法，提出了LPV-PID控制后验稳定性分析策略。结果表明，优化得到的控制参数满足倾转角/前飞速度平滑增益调度需求,基于LPV-PID控制的倾转旋翼机闭环纵向增稳系统满足稳定性条件。在此基础上，基于LPV-PID控制方法，开展了倾转旋翼机全倾转试飞试验。试验结果表明，基于LPV-PID控制方法，倾转旋翼机在整个倾转过渡过程中俯仰姿态变化平稳、俯仰姿态跟踪精度高，满足倾转过渡指标。

关键词： 倾转旋翼机; 纵向增稳优化设计; LPV-PID; 倾转过渡; 试验试飞

本文引用格式

段登燕 , 苏小恒 , 严峰 , 刘毅 , 陈国军 . 考虑飞行品质的倾转旋翼机LPV-PID控制设计方法[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33848

Abstract

This paper presents a design method of LPV-PID control for tiltrotor aircraft considering flight qualities. Firstly, a linear variable parameter (LPV) model based on tilt angle/forward velocity gain scheduling is obtained for tiltrotor aircraft by linearization on the basis of flight dynamics model and tilt transition corridor. Furthermore, based on simulated annealing algorithm, the optimal design method of longitudinal channel control parameters for tiltrotor aircraft considering flight qualities is developed. The optimal control parameters under different flight conditions in the transition corridor are obtained. Furthermore, based on the LPV control theory, an LPV-PID control method based on tilt angle/forward velocity gain scheduling is formed and a posterior stability analysis strategy of LPV-PID control is proposed. The results show that the optimized control parameters meet the smooth gain scheduling requirements of tilt angle/forward velocity, and the closed-loop longitudinal stability augmentation system based on LPV-PID control meets the stability conditions. On this basis, based on the LPV-PID control method, a tilt flight test of tiltrotor aircraft is carried out. The experimental results show that the pitch attitude of tiltrotor aircraft changes smoothly and has high tracking accuracy during the whole tilt transition process based on LPV-PID control method, which satisfies the tilt transition index.

Key words： Tiltrotor aircraft; longitudinal stability augmentation optimization design; LPV-PID; tilt transition; flight test

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