典型飞行状态桨榖交变载荷和机体振动水平预估  

Prediction of Hub Alternating Loads and Airframe Vibration Response in Typical Flight Conditions

作　　者：夏双满 林长亮 张体磊 崔荫 袁胜弢 XIA Shuang-man;LIN Chang-liang;ZHANG Ti-lei;CUI Yin;YUAN Sheng-tao(Aircraft Design and Research Institute,AVIC Harbin Aircraft Industry Group Co.,Ltd.,Harbin 150066,China;The Military Representative Office of the Army Aviation Department in Harbin Region,Harbin 150066,China)

机构地区：[1]航空工业哈尔滨飞机工业集团有限责任公司飞机设计研究所,哈尔滨150066 [2]陆军航空军事代表室驻哈尔滨地区军事代表室,哈尔滨150066

出　　处：《科学技术与工程》2021年第8期3387-3392,共6页Science Technology and Engineering

基　　金：黑龙江省自然科学基金(JQ2020E006)。

摘　　要：为了评估直升机机体振动水平,开展了桨毂交变载荷预估工作,以某型直升机为算例,采用综合气弹分析方法对其典型飞行状态下进行桨毂振动载荷计算;通过模块化方法建立某型直升机有限元模型,以计算一阶通过频率下的桨毂振动载荷为输入,预估了机体驾驶员座椅处的振动响应,并与相同飞行状态实测振动水平做了对比分析。结果表明:机体响应预测结果与飞行实测结果一致性较好,计算结果符合该型机机体振动随飞行速度变化的规律。In order to predict the vibration level of helicopter,the hub alternating loads were predicted.The hub alternating loads of helicopter were calculated in the typical flight conditions by the comprehensive aeroelastic analysis method.The finite element model of helicopter was established by the modular method,and the vibration response was calculated under the first pass frequency hub load.The vibration response at the pilot seat of the helicopter was estimated and compared with flight test results.The results show that the predicted results are in good agreement with the test results,and the calculated results are in accordance with the law that the vibration of the airframe changes with the flight speed.

关 键 词：直升机 桨榖交变载荷 振动响应 飞行实测 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]