直升机旋翼/机体动稳定性研究进展  

RESEARCH PROGRESS OF DYNAMIC STABILITY OF HELICOPTER ROTOR/AIRFRAME

作　　者：贺天鹏[1] 李书[1] 李小龙[2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国航天标准化与产品保证研究院,北京100071

出　　处：《力学与实践》2013年第3期1-19,共19页Mechanics in Engineering

基　　金：国家863计划(2012AA112201);国家自然科学基金项目(10772013);航空科学基金项目(20100251007);中央高校基本科研业务费专项资金资助项目

摘　　要：首先对直升机旋翼/机体动不稳定性问题的种类进行了简要概述,包括旋翼挥舞/变距、变距/摆振、挥舞/摆振和挥舞/摆振/变距耦合等孤立旋翼动不稳定性问题,以及直升机地面共振和空中共振等旋翼/机体耦合动不稳定性问题,然后分别从气动力与结构的高精度数值模型、动稳定性的计算分析方法和实验模型测试3个方面详细介绍了直升机旋翼/机体动不稳定性问题的研究现状,并着重讨论了直升机旋翼/机体动稳定性分析技术最近的主要研究方向:耦合CFD(computational fluid dynamics)/CSD(computational structural dynamics)的直升机旋翼气弹动稳定性分析、复合材料旋翼动稳定性分析及其材料不确定性影响、带减摆器的旋翼/机体动稳定性分析和先进直升机构型的旋翼/机体动稳定性分析,最后对直升机旋翼/机体动稳定性研究的发展趋势进行了展望.This paper first briefly reviews the types of the dynamic instability of helicopter rotor/airframe, including the isolated blade dynamic instabilities such as the rotor flap-pitch coupling, pitch-lag instability, the coupled flap-lag aeroelastic instability, the flap-lag-pitch coupled instability, and the coupled rotor/airframe instabilities, such as the ground resonance and the air resonance. The related studies are reviewed from 3 aspects, the aerodynamic and structural nmnerical models with high precisions, the numerical methods ot dynamic stability, and the model testing. The major fields of the analytical technology for dynamic stability of helicopter rotor/airframe are discussed, including the rotor aeroelastic stability analysis using the coupled computational fluid dynamics/computational structural dynamics, the dynamic stability analysis of composite rotor with consideration of material uncertainty, the dynamic stability analysis of coupled rotor/airframe with lag damper, and helicopters with advanced configurations. In the end, the future development of dynamic stability of helicopter rotor/airframe is commented.

关 键 词：直升机 动稳定性 地面共振 空中共振 材料不确定性 

分 类 号：V214.34[航空宇航科学与技术—航空宇航推进理论与工程]