随积冰历程的机翼蒙皮载荷实验研究

李钊; 杨广珺; 蒋锋

doi:10.11729/syltlx20200074

随积冰历程的机翼蒙皮载荷实验研究

doi: 10.11729/syltlx20200074

李钊^1,,
杨广珺^{2, 3, ,},
蒋锋¹

1.
西北工业大学航空学院, 西安 710072
2.
西北工业大学无人机特种技术国防科技重点实验室, 西安 710068
3.
中国空气动力研究与发展中心结冰与防除冰重点实验室, 四川绵阳 621000

基金项目:

结冰与防除冰重点实验室开放课题 IADL20190406

详细信息

作者简介:
李钊(1990-), 男, 陕西渭南人, 博士研究生。研究方向: 飞行器总体设计。通信地址: 陕西省西安市友谊西路127号西北工业大学航空学院(710072)。E-mail: lizhao0125@163.com

通讯作者:
杨广珺, E-mail: yanggj_1031@nwpu.edu.cn

中图分类号: V216.5⁺1;V211.71
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- 被引次数: 0
出版历程
- 收稿日期: 2020-06-12
- 修回日期: 2020-08-21
- 刊出日期: 2021-06-25

Experimental analysis on aero-loading of wing skin with icing accretion

LI Zhao^1
,,
YANG Guangjun^{2, 3
, ,},
JIANG Feng¹

1.
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
2.
National Key Laboratory of Science and Technology on UAV, Northwestern Polytechnical University, Xi'an 710068, China
3.
Key Laboratory of Icing and Anti/De-icing, China Aerodynamics Research and Development Centre, Mianyang Sichuan 621000, China

摘要

摘要: 积冰改变了翼型的气动外形和绕流流场，使得机翼气动载荷分布产生动态变化。蒙皮作为气动载荷的承受及传递对象，会在气动载荷的动态作用下产生不同的振动响应。以某大弯度翼型为研究对象，提取了典型积冰增长过程中尾缘上下蒙皮振动特征，采用载荷谱方法研究积冰全历程的蒙皮振动及流场变化特性，并分析了不同材质的蒙皮在结冰不同阶段的响应及结构稳定性。结果表明：不同材质蒙皮对冰致脱体涡及后缘分离涡具有不同的载荷感知特性；刚性蒙皮载荷谱及其能量相对集中，柔性蒙皮载荷相对分散；随着积冰增多、冰角增长，脱体涡主频逐渐前移，冰角表面小冰枝引起宽幅高频振动；前缘脱体涡与尾迹掺混造成翼型后缘绕流载荷能量增加。
- 积冰 /
- 冰致气流振荡 /
- 气动载荷 /
- 蒙皮响应 /
- 能谱分布
Abstract: Ice accretion changes the aerodynamic shape and flow field of the airfoil, which makes the aerodynamic load distribution of the wing change dynamically. The skin, as the object of bearing and transferring aero-loading, produces different vibration responses under its dynamic action. Taking a large camber and thick airfoil as an object, the vibration characteristics of the upper and lower skins of the trailing edge under the typical icing condition are extracted, the load spectrum is used to study the skin vibration and flow field changes, and the structural stability of different skin is investigated. The results show that: Different skins have different load sensing performance for the ice-induced detached vortices and trailing edge separated vortices; the load spectrum and energy are relatively concentrated for the rigid skin while scattered for the flexible skin; as the ice accretes, the dominant frequency of detached vortices decreases slightly, substrate ice causes wide-width and high-frequency vibration, and the mixing of detached vortices and the wake results in the increase of the loading energy around the trailing edge.
- ice accretion /
- ice-induced vibration /
- aero-loading /
- skin response /
- energy spectra distribution

HTML全文

图 1 0.3 m×0.2 m结冰风洞外形

Figure 1. Diagram of icing wind tunnel FL-16y

下载: 全尺寸图片幻灯片

图 2 实验模型及传感器安装位置

Figure 2. Test model and accelerometer position

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图 3 翼型的结冰风洞实验结果

Figure 3. Ice shapes of hybrid airfoil at -2 ℃ and -7 ℃

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图 4 结冰后的翼型绕流流场变化过程及蒙皮振动示意

Figure 4. Flow field and skin vibration in a period

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图 5 采用CFD得到的翼型压力脉动频率

Figure 5. FFT analysis of the pressure oscillation frequencies at different positions

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图 6 不同材质蒙皮的加速度测量值

Figure 6. Graph of acceleration over time at different locations

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图 7 吹气阶段不同蒙皮的翼型前缘响应

Figure 7. The vibration of CF and AA skin without ice

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图 8 铝合金蒙皮典型时间点频率响应

Figure 8. The vibration frequency of aluminum alloy skin at different times

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图 9 碳纤维蒙皮典型时间点频率响应

Figure 9. The vibration frequency of carbon fiber skin at different times

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图 10 未结冰(-30 s)、结冰中(60 s)、结冰后(90 s)压力分布及流线

Figure 10. Pressure distribution and streamline obtained by CFD

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表 1 实验参数

Table 1. Parameters for tests

来流总压p/Pa	来流速度v_∞/(m·s^-1)	迎角α/(°)	液态水含量LWC/(g·m^-3)	平均液滴直径MVD/μm	结冰时间t/s
96 573	90.0	4	0.5	25	180

下载: 导出CSV

表 2 蒙皮模态分析结果

Table 2. Modal analysis results

	一阶频率	二阶频率	三阶频率	四阶频率
铝合金AA	485.57	485.57	579.88	708.66
碳纤维CF	427.28	427.28	509.38	623.59

下载: 导出CSV

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