基于动力学特性优化的直升机航向操纵系统减振效果验证  

Verification of Vibration Reduction Effect of Helicopter Heading Control System based on Dynamic Characteristics Optimization

作　　者：陈浩[1] 王哲人 马小艳[1] 王之瑞 CHEN Hao;WANG Zheren;MA Xiaoyan;WANG Zhirui(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Certain Troop of the PLA,Harbin 150066,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]中国人民解放军某部队,黑龙江哈尔滨150066

出　　处：《直升机技术》2024年第4期1-3,9,共4页Helicopter Technique

摘　　要：基于结构动力学基本原理及其影响因素,对直升机在飞行过程中出现的航向操纵拉杆支座断裂以及后舱脚蹬振动较大的问题,通过航向操纵系统增加配重和部分拉杆更换为球柔钢索这两种方式,优化航向操纵系统的安装动特性。试飞验证结果表明,两种方式均能有效降低拉杆振动,进而明显改善支座受载和脚蹬处的振动。In view of the phenomena of fracture of the heading control pull rod support and large vibration of pedal in the rear cabin during flight of a helicopter,the mounting dynamic characteristics of the heading control system were optimized by increasing the counterweight of the heading control system and replacing part of the pull rod with a ball cable.The test flight verification results showed that the two methods could effectively reduce the vibration of the pull rod,and then significantly improve the vibration of the support loading and pedal.

关 键 词：直升机 航向操纵系统 动特性 增加配重 球柔钢索 试飞验证 

分 类 号：V214.33[航空宇航科学与技术—航空宇航推进理论与工程] V227