直升机颤振试飞激励系统的设计与实现  

Design and Implementation of Helicopter Flutter Flight Excitation System

作　　者：李育丽 寇宝智 梁海洲 LI Yu-li;KOU Bao-zhi;LIANG Hai-zhou(Chinese Flight Test Establishment,Xiʹan 710089,China)

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《装备环境工程》2020年第9期166-172,共7页Equipment Environmental Engineering

摘　　要：针对电传直升机结构动力学稳定性和飞行品质相关试飞科目的需求,首次设计了采用基于PowerPC和国产嵌入式实时操作系统ACoreOS架构的直升机颤振试飞激励系统。针对直升机复杂传动关系,采用多通道耦合激励输出技术和可靠的多种保安监控策略,实现了高精度、高可靠性的激励输出。通过仿真测试及设备实际工程应用,验证了该直升机颤振试飞激励系统设计的有效性和设备的适用性。为有效降低试飞风险,提高试飞效率,缩短试飞周期,提供强有力的支持保障。The work aims to design a helicopter flutter flight excitation system based on the architecture of PowerPC and the domestic embedded real-time operating system ACoreOS for the first time to meet the requirements of fly-by wire helicopter flight test subjects about structural dynamic stabilities and flying quality.In view of the complex transmission relationship of helicopters,multi-channel coupled excitation output technology and various security monitoring measures were applied to realize the high-precision and reliability excitation output.The effectiveness of design and the applicability of the equipment were verified by the simulation tests and the practical engineering applications.The helicopter excitation system provides strong support and guarantee for effectively reducing the flight test risk and test cycle and improving the flight test efficiency.

关 键 词：直升机 耦合 颤振激励 保安监控 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]