某型综合试验直升机旋翼试飞测试系统设计  

Research and Design of the Helicopter Rotor Flight Test Measurement System

作　　者：虞汉文[1] 朱洪兴 顾文标[1] 段刚[1] YU Hanwen;ZHU Hongxing;GU Wenbiao;DUAN Gang(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Beijing Infotronix Ltd.Co.,Beijing 100098,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]北京世纪兴元科技发展有限公司,北京100098

出　　处：《直升机技术》2018年第4期65-68,44,共5页Helicopter Technique

摘　　要：针对某型综合试验直升机对旋翼系统测试的需求,基于编码正交频分复用调制技术、空心感应线圈供电和光信号传输等技术开展测试技术研究,解决有限安装空间下的旋转部件测试信号高精度实时测量的难题。研制的旋翼、尾桨测试系统通过地面试验和飞行试验验证,满足试验机试飞测试的要求,为开展研究性试飞奠定了基础。For the requirements of flight test measurement to the rotor system of the comprehensive testing helicopter,based on the technology of COFDM,induced electricity and light signal transmission to conduct measurement methods research and get solution of real time accurate measurement being fit for the special narrow space and high rotating parts. In the end,the products of measurement system had been developed and checked out all right during the ground tests and flight tests.

关 键 词：直升机旋翼 测试系统 COFDM 感应供电 光信号传输 

分 类 号：V217.2[航空宇航科学与技术—航空宇航推进理论与工程] V216