飞机全动平尾颤振特性风洞试验

doi:10.7527/S1000-6893.2014.0250

气动弹性力学

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飞机全动平尾颤振特性风洞试验

钱卫^1,2, 张桂江¹, 刘钟坤¹

1. 中航工业沈阳飞机设计研究所, 沈阳 110035;
2. 大连理工大学航空航天学院, 大连 110624

收稿日期:2014-07-30 修回日期:2014-09-07 出版日期:2015-04-15 发布日期:2014-11-15
通讯作者: 钱卫Tel.: 0411-84709105 E-mail: sy_qianwei@139.com E-mail:sy_qianwei@139.com
作者简介:钱卫男, 研究员。主要研究方向: 飞机气动弹性力学。Tel: 0411-84709105 E-mail: sy_qianwei@139.com
基金资助:
国家自然科学基金(91330206)

Flutter characteristics for aircraft all-movable horizontal tail through wind tunnel test

QIAN Wei^1,2, ZHANG Guijiang¹, LIU Zhongkun¹

1. AVIC Shenyang Aircraft Design & Research Institute, Shenyang 110035, China;
2. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 110624, China

Received:2014-07-30 Revised:2014-09-07 Online:2015-04-15 Published:2014-11-15
Supported by:
National Natural Science Foundation of China(91330206)

摘要/Abstract

摘要：

高机动飞机全动平尾颤振设计的重要手段就是颤振模型风洞试验。针对一个飞机的全动平尾,采用了单独平尾和中央固支的后机身-平尾组合体两种方案的低速颤振风洞试验,研究平尾的基本颤振耦合机理以及后机身垂尾气动力干扰的影响。然后采用半模跨声速颤振风洞试验研究马赫数对颤振特性的影响和机翼干扰对平尾颤振边界的影响。介绍了低、高速颤振模型的设计和风洞试验的结果,并综合形成了完整的平尾颤振特性规律,尤其在跨声速颤振风洞试验中,使用不同超重系数的颤振模型,研究了质量参数对颤振边界的影响规律。风洞试验结果显示,全动平尾颤振特性研究必须考虑后机身的弹性支持,并且需要使用不同的模型方案考虑机身、机翼和垂尾的气动力干扰,跨声速风洞模型需要考虑超重系数的影响。该研究获得了全动平尾颤振特性的一般规律,可作为相关飞行器设计的参考。

关键词: 颤振, 全动平尾, 风洞试验, 缩比模型, 跨声速风洞, 低速风洞

Abstract:

Flutter wind tunnel test is the main technique in the flutter design process for the high maneuver aircraftall-movable horizontal tail. The low-speed flutter model of an all-movable horizontal tail has two kinds of configurations during wind tunnel test (single horizontal tail and horizontal tail with fixed rear fuselage). In low-speed wind tunnel, the basic flutter mode of the horizontal tail and the aerodynamic influence of the rear fuselage are investigated and verified. A semi-span dynamic scaled flutter model is used in transonic wind tunnel. The effect of Mach number and the aerodynamic influence of wing on the flutter boundary are investigated and verified. In this paper, details of flutter models' design are shown, and the wind tunnel test results indicate full flutter characteristics of the all-movable horizontal tail. Especially in transonic flutter wind tunnel test, the effect of mass parameter (Newton number) on flutter boundary is investigated using flutter model with different mass overload factors. Wind tunnel test results show that the flutter characteristic of the all-movable horizontal tail must consider the rear fuselage elastic support. Different configurations of flutter model are used to consider the influences of fuselage, wing and vertical fin. Transonic flutter model has to consider the mass overload factor. In general, all the flutter characteristics for the all-movable horizontal tail obtained through wind tunnel test could be taken as a reference in other aircraft design.

Key words: flutter, all-movable horizontal tail, wind tunnel test, scaled model, transonic wind tunnel, low-speed wind tunnel

中图分类号:

钱卫, 张桂江, 刘钟坤. 飞机全动平尾颤振特性风洞试验[J]. 航空学报, 2015, 36(4): 1093-1102.

QIAN Wei, ZHANG Guijiang, LIU Zhongkun. Flutter characteristics for aircraft all-movable horizontal tail through wind tunnel test[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1093-1102.

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E-mail：hkxb@buaa.edu.cn

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飞机全动平尾颤振特性风洞试验

Flutter characteristics for aircraft all-movable horizontal tail through wind tunnel test

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