基于耦合动力学要求的旋翼阻尼器特性分析

郭俊贤; 向锦武; 覃海鹰

基于耦合动力学要求的旋翼阻尼器特性分析

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2. 中国直升机设计研究所, 景德镇 333001

详细信息

作者简介:
郭俊贤(1966-),男,江西吉安人,博士生,gjx66@yahoo.com.cn.

中图分类号: V 211.47
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- 被引次数: 2
出版历程
- 收稿日期: 2010-04-28
- 网络出版日期: 2011-09-30

Rotor damping analysis based on helicopter dynamic requirement with rotor/fuselage coupling

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2. China Helicopter Research and Development Institute, Jingdezhen 333001, China

摘要

摘要: 旋翼阻尼特性是直升机动力学问题的要素之一,根据全机动力学设计要求,进行地面共振和旋翼/动力/传动扭振系统稳定性分析,并据此提出旋翼系统阻尼特性参数设计要求.分析了粘弹性阻尼器和液压阻尼器的特点,研究了阻尼器刚度和阻尼对全机耦合动力学的影响;通过比较不同孔径节流孔的阻尼特性,确定了阻尼器设计方案.计算分析结果以及阻尼器样件的性能试验和机上试验验证结果表明:阻尼特性能够满足地面共振和旋翼/动力/传动扭振系统稳定性要求,并可实现其用于桨叶折叠的功能要求.
- 直升机 /
- 耦合动力学 /
- 旋翼 /
- 阻尼
Abstract: The rotor damping is one of the key points for a helicopter dynamic design. An introduction to the theoretical and practical study of one of the helicopter dynamic problems, which describesd the development of the rotor damping based on the helicopter dynamic with rotor/fuselage coupling that contains the stability analysis of ground resonance and the stability of rotor/power/transmission coherent was given. Based on the dynamic requirement of rotor/frame, damping analysis of the elasto-damper and the fluid-damper, which considered the effect of the stiffness and the damping was presented. The parametric sensitivity of the damper stiffness and damping was estimated. With constraints from engine control and ground resonance, the different effect was given with various available designs.Calculating and testing results performed demonstrating that, as solution to the dynamic problem, the damping with suitable orifice design for a variable liquid damper is reasonable for the helicopter dynamic problem solution and rotor blade folding.
- helicopter /
- coupling dynamics /
- rotor /
- damping

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参考文献(1)

[1] Ivchin V.Analysis of lag motion damping for upgraded Mil-24 main rotor blades in hover,level and maneuvering flight based on flight test results .AHS-2001-160,2001 [2] Guo Junxian,Xiang Jinwu.Composite rotor blade design optimization for vibration reduction with aeroelastic constraints[J].Chinese Journal of Aeronautics,2004,17(3):152-158 [3] Phuriwat A I,Gandhi F.Reduction of helicopter vibration through cyclic control of variable orifice damper .AHS-2002-94,2002 [4] 郭俊贤,胡茂和,艾剑波.某型直升机动力学解决方案 //第25届直升机年会会议论文集.景德镇:中国航空学会,2009:383-386 Guo Junxian,Hu Maohe,Ai jianbo.The scheme of XX helicopter dynamic problem //The 25th National Annual Conference on Helicopter.Jingdezhen:Chinese Society of Aeronautics and Astronautics,2009:383-386(in Chinese) [5] Hu Guocai,Xiang Jinwu,Zhang Xiaogu.Analytical model of elastomeric lag damper kinematic coupling and Its effect on helicopter air resonance in hover[J].Chinese Journal of Aeronautics,2002,15(1):27-32

施引文献

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