共轴高速直升机/发动机交联控制方法研究  

Research on Integrated Control Method of Coaxial High Speed Helicopter/Engine

作　　者：谌昱[1] 宋劼 张海波[2] 杨波[1] Chen Yu;Song Jie;Zhang Haibo;Yang Bo(China Helicopter Research and Development Institute,Jingdezhen 333000,China;Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333000 [2]南京航空航天大学,江苏南京210016

出　　处：《航空科学技术》2024年第2期68-74,共7页Aeronautical Science & Technology

摘　　要：针对常规的旋翼总距前馈方法难以有效实现共轴高速直升机/发动机快速交联控制的问题,本文提出并设计了适用于共轴高速直升机/发动机的新型交联控制方法。首先,基于共轴高速直升机/发动机综合仿真平台,揭示不同运行工况下,共轴双旋翼、推力桨操纵输入、发动机燃油输入变化规律;其次,在此基础上,提出了综合考虑共轴双旋翼、推力桨桨距的增益自调节交联控制方法,并针对不同的运行工况,开展了数值仿真验证。结果表明,在中等、高速度飞行时,相比于常规的旋翼总距前馈,新型交联控制方法可使动力涡轮转速的超调与下垂量减小36%与70%,可使直升机/发动机快速交联控制品质更优,进一步提升直升机/发动机综合系统的控制品质。In order to deal with the problem that the conventional collective pitch feedforward method is difficult to effectively accomplish the fast integrated control of coaxial high-speed helicopter/turboshaft engine,a novel integrated control suitable for coaxial high-speed helicopter/engine is proposed and designed.Firstly,based on the comprehensive simulation platform of coaxial high-speed helicopter/turboshaft engine,the variation laws of control inputs of coaxial main rotors and propeller,engine fuel flow under different operating conditions are revealed.Then,an integrated control method with gain self-regulating function is proposed.It consist of the collective pitch of coaxial main rotors and propeller simultaneously.The numerical simulation is carried out under different operating conditions.The results demonstrate that when the high-speed helicopter operates at medium and high speed,compared with the conventional collective pitch feedforward,the proposed integrated control method can decrease the overshoot and drop of power turbine speed by about 36%and 70%respectively,and the fast control quality is superior,which further improve the control quality of the integrated helicopter/engine system.

关 键 词：共轴高速直升机 涡轴发动机 交联控制 双旋翼 推力桨 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]