直升机吊挂飞行中载荷摆动控制方法研究  

Research on Slung-load Swing Control Method in Helicopter Suspension Flight

作　　者：张松 马钊 张辉 ZHANG Song;MA Zhao;ZHANG Hui(Department of Flight Control System,AVIC Xi’an Flight Automatic Control Research Institute,Xi’an 710065,China)

机构地区：[1]航空工业西安飞行自动控制研究所飞行控制系统部,西安710065

出　　处：《航空工程进展》2022年第2期57-63,共7页Advances in Aeronautical Science and Engineering

基　　金：工信部民机专项科研项目(MJ-2016-S-40)。

摘　　要：当直升机的吊挂载荷较大时,机体和吊挂相互耦合将会影响直升机的操纵性和稳定性。飞行员对直升机的操纵会引起吊挂载荷摆动,导致直升机产生剩余振荡,飞行员处理不当极易出现飞行员诱发振荡(PIO)现象。以某直升机为研究对象,通过一些假设简化直升机吊挂模型,提出一种面向工程应用的控制方法;以显模型跟随控制方法为基础架构,结合自适应控制和输入整形技术,对控制方法进行仿真分析。结果表明:该控制方法给飞行员提供了良好的操纵性,同时能够解决吊挂飞行时存在的剩余振荡问题。For helicopter with large suspension load,the coupling between helicopter body and load will significantly affect the maneuverability and stability of the helicopter. The suspension load swing of helicopter can be induced by the handling of pilot,which leads to the residual oscillation of the helicopter,and the pilot induced oscillation(PIO)phenomenon can be induced by improper hanging of pilot. A certain helicopter is taken as the research object,and the suspension model of helicopter is simplified through some assumptions. A control method oriented to engineering application is proposed. The explicit model-following control method is taken as the infrastructure,and the adaptive control and input-shaping technique are combined to perform the simulation analysis for the control method. The results show that the proposed control method not only can provide the good maneuverability for pilot,but also solve the problem of the residual oscillation of the helicopter.

关 键 词：直升机控制 吊挂飞行 模型跟随 自适应控制 输入整形 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]