电传直升机激励技术的实现与应用  

Implementation and Application of Fly-by-wire Helicopter Excitation Technology

作　　者：寇宝智 梁海州[1] 雷鸣[1] KOU Bao-zhi;LIANG Hai-zhou;LEI Ming(Flight Test Technology Institute,Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院飞机所,西安710089

出　　处：《科技和产业》2021年第6期278-283,共6页Science Technology and Industry

摘　　要：针对某电传直升机结构动力学稳定性试飞中的激励需求,通过参考固定翼电传飞机颤振激励系统的设计及激励实现原理,结合直升机特殊激励接口、旋翼运动和舵机控制耦合方程,设计出合理的激励方案。同时通过不同试飞科目需求的激励信号设计及实时激励任务中信号切除工作逻辑设计,提高了激励实施的适用性和飞行试验的安全性。最后通过某型直升机的气动伺服弹性稳定性试飞的工程应用验证了该激励技术的有效性。As the requirements of helicopter structural dynamic stability flight tests,a reasonable excitation scheme based on the special test interfaces of helicopter flight control system and coupled equations of rotor motion and servo control was designed by referring to the implementation of fixed wing aircraft’s flutter excitation system.The feasibility of excitation applications and flight test safety were improved by the designs of different excitation signals for various tests and emergency cutoff strategy in real time excitation tasks.At last,the effectiveness of helicopter excitation technology was verified by a helicopter flight test case about aeroservoelasticity stability.

关 键 词：直升机激励 耦合 气动伺服弹性 正弦扫频激励 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]