Wind tunnel test technique for aerodynamic stability of refueling hose-drogue of aerial tanker

HUANG Xia; LU Jing; ZHANG Haiyou; WANG Xue

doi:10.7638/kqdlxxb-2018.0165

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Wind tunnel test technique for aerodynamic stability of refueling hose-drogue of aerial tanker

更新时间：2026-05-28

- Wind tunnel test technique for aerodynamic stability of refueling hose-drogue of aerial tanker
- Vol. 37, Issue 1, Pages: 140-146(2019)
- 作者机构：
  
  1. 中国空气动力研究与发展中心,四川,绵阳,621000
  2. 第一飞机设计研究院,陕西,西安,710089
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0165
  CLC： V211.7
- Published：2019
- 稿件说明：
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黄霞, 卢静, 张海酉, 王学. 空中加油机加油软管锥套气动稳定性风洞试验技术[J]. 空气动力学学报, 2019, 37(1): 140-146.

HUANG Xia, LU Jing, ZHANG Haiyou, et al. Wind tunnel test technique for aerodynamic stability of refueling hose-drogue of aerial tanker[J]. 2019, 37(1): 140-146.
黄霞, 卢静, 张海酉, 王学. 空中加油机加油软管锥套气动稳定性风洞试验技术[J]. 空气动力学学报, 2019, 37(1): 140-146. DOI： 10.7638/kqdlxxb-2018.0165.

HUANG Xia, LU Jing, ZHANG Haiyou, et al. Wind tunnel test technique for aerodynamic stability of refueling hose-drogue of aerial tanker[J]. 2019, 37(1): 140-146. DOI： 10.7638/kqdlxxb-2018.0165.

摘要

软式加油方式中加油软管锥套受气流影响会发生气动不稳定现象，严重影响空中加/受油的成功率和安全性，其中加油机的尾流场是影响软管锥套稳定性的主要因素。本文研究了空中加油机加油软管锥套的气动稳定性风洞试验方法，建立并分析了相似准则，给出了双目系统测量软管锥套位移的具体方法，利用自动舵机实现了加油软管自动收放，形成了完整的加油软管锥套气动稳定性风洞试验技术，并将其应用于某型加油机加油吊舱、中心线平台等部件的选型优化。结果表明，该试验技术能有效模拟处于加油机尾流场下的软管锥套收放过程和固定管长时的气动稳定性，试验获得的锥套下沉量和振动幅值明确了不同加油吊舱、中心线平台构型的优劣性，能够为加油机关键加油部件选型优化及飞行试验提供可靠的试验数据。

Abstract

While a refueling hose-drogue is affected by airflow

aerodynamic instability phenomenon occurs

which has serious influences on the safety and success rate of refueling flight. The wake field of the tanker is the most important factor affecting the hose-drogue stability. The wind tunnel test technique for aerodynamic stability of refueling hose-drogue of aerial tanker is studied in this paper. The similarity criteria is established and analyzed

and the displacement measurement method by binocular system is presented. The retraction-extension of refueling hose is implemented by automatic steering engine

and the complete wind tunnel test technique is formed for aerodynamic stability of refueling hose-drogue. This technique is applied to the configuration optimization of refueling fuselage and central platform for one aerial tanker. The results show that this test technique can simulate the hose-drogue stability within tanker's wake field for the retraction-extension phase and fixed length state. The vertical sinkage value and vibration amplitude obtained by the test can evaluate different fuselage and central platform configurations

and can provide reliable data for flying tests and configuration optimizations of key refueling parts.

关键词

Keywords

references

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