旋翼/平尾气动干扰对直升机配平特性的影响分析

谭剑锋; 吴超; 王浩文; 林长亮

doi:10.13700/j.bh.1001-5965.2015.0770

旋翼/平尾气动干扰对直升机配平特性的影响分析

doi: 10.13700/j.bh.1001-5965.2015.0770

1.
南京工业大学机械与动力工程学院, 南京 211816
2. 南京航空航天大学航空宇航学院, 南京 210016
3. 清华大学航天航空学院, 北京 10008
4. 中航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

基金项目: 国家自然科学基金（11502105）；江苏省自然科学基金（BK20161537）；江苏省普通高校自然科学研究计划（15KJB130004）

详细信息

作者简介:
谭剑锋,男,博士,讲师。主要研究方向:旋翼空气动力学与结构动力学、风力机空气动力学。Tel.:025-58139357,E-mail:Jianfengtan@njtech.edu.cn;吴超,男,博士研究生。主要研究方向:直升机飞行力学、直升机仿真与控制。E-mail:wuchao_nuaa@163.com;王浩文,男,博士,教授,博士生导师。主要研究方向:旋翼动力学、结构强度及振动载荷分析。Tel.:010-62792661,E-mail:bobwang@mail.tsinghua.edu.cn;林长亮,男,博士,工程师。主要研究方向:旋翼结构动力学。E-mail:lclnuaa@nuaa.edu.cn

通讯作者:
谭剑锋,Tel.:025-58139357,E-mail:Jianfengtan@njtech.edu.cn

中图分类号: V211.52
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- 被引次数: 1
出版历程
- 收稿日期: 2015-11-23
- 修回日期: 2016-01-27
- 网络出版日期: 2016-11-20

Analysis on influence of rotor/empennage aerodynamic interaction on helicopter trim characteristic

1.
School of Mechanical and Power Engineering, Nanjing Tech University, Nanjing 211816, China
2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
3. School of Aerospace, Tsinghua University, Beijing 10008
4. Institute of Aircraft Design, AVIC Harbin Aircraft Industry Group Corporation, Harbin 150066, China

摘要

摘要: 旋翼/平尾气动干扰建模是直升机全机配平模型和飞行动力学模型的核心内容。常规全机配平模型主要通过旋翼下洗流或诱导速度等方式间接考虑旋翼对平尾的气动干扰作用，但未充分考虑旋翼对平尾非定常气动干扰产生的非线性气动载荷，因而仍难于准确体现旋翼/平尾气动干扰对全机配平特性的影响。为此本文基于非定常面元/黏性涡粒子法，通过在平尾面元中增加由旋翼和平尾尾迹时变干扰产生的非定常压力项，建立旋翼/平尾气动干扰模型，直接计算平尾非线性气动载荷，并耦合基于GA/LM混合优化的直升机全机配平方法，构建旋翼/平尾气动干扰作用下的直升机全机配平特性分析方法。通过计算UH-60A直升机的旋翼操纵量和机体姿态，并与试验测试值对比验证本文方法的准确性。通过与基于诱导速度考虑旋翼/平尾气动干扰的直升机配平结果比较表明，后者难于体现直升机低速纵向操纵量和机体俯仰角突增现象，而本文方法能较好地体现直升机低速纵向操纵量和机体俯仰角突增，且与OH-6A、EH-101等试验测量的特性一致。研究不同平尾构型对旋翼/平尾气动干扰下直升机全机配平特性的影响，分析表明低平尾产生较大的低速纵向操纵量突增，而高平尾则增加高速纵向操纵量；前置平尾产生较大的低速纵向操纵量突增，右旋直升机的右置平尾有利于减小低速纵向操纵量突增和机体俯仰角。
- 平尾气动 /
- 黏性涡粒子法 /
- 直升机配平 /
- 旋翼操纵 /
- 机体姿态
Abstract: Unsteady aerodynamic interaction of rotor and empennage is the core content of helicopter trim model and flight dynamic model. The rotor/empennage aerodynamic interaction effect was considered indirectly through rotor inflow or induced velocity of rotor wake in classical trim method. However, the nonlinear airload induced by the unsteady aerodynamic interaction was not fully taken into account, and it is then difficult to reflect the influence of the rotor/empennage aerodynamic interaction on the trim characteristic. Therefore, based on unsteady panel/viscous vortex particle method, a rotor/empennage unsteady aerodynamic interactional model is established by adding an unsteady pressure term into empennage panel which is induced by unsteady interaction of rotor and empennage wake, and the nonlinear airload on empennage is simulated. The helicopter trim characteristic analysis method under rotor/empennage aerodynamic interaction is then established by coupling with helicopter trim method based on GA/LM hybrid optimization. The control of rotor and attitude of fuselage of UH-60A are simulated and compared with the flight test data to validate the present method. Compared with the result of the classic helicopter trim method in which rotor/empennage aerodynamic interaction is indirectly accounted through induced velocity, it is shown that the increase of longitudinal control and fuselage attitude is not simulated by the classic helicopter trim method; however, the phenomenon is captured by the present method, and is consistent with the tested characteristics of OH-6A, EH-101, etc. The influence of empennage's type on helicopter trim characteristic is then analyzed, and it is shown that the increase of rotor longitudinal control is great with low-set empennage, forward-set empennage in low-speed forward flight, and high-set empennage in high-speed forward flight. Start-set empennage for right revel rotor is useful to decrease the increasement of longitudinal control and fuselage attitude in low-speed forward.
- empennage aerodynamics /
- viscous vortex particle method /
- helicopter trim /
- rotor control /
- fuselage attitude

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