不同对接速度下软式加油管锥套运动特性数值模拟研究

陈乐乐; 刘学强

doi:10.7638/kqdlxxb-2016.0038

不同对接速度下软式加油管锥套运动特性数值模拟研究

doi: 10.7638/kqdlxxb-2016.0038

南京航空航天大学航空宇航学院, 江苏南京 210016

基金项目:

江苏省普通高校研究生科研创新计划资助项目 CXLX13_133

详细信息

作者简介:
陈乐乐(1986-), 女, 山东人, 博士研究生, 主要研究方向:计算空气动力学.E-mail:xchen1986@hotmail.com

中图分类号: V221.3
计量
- 文章访问数: 226
- HTML全文浏览量: 42
- PDF下载量: 552
- 被引次数: 0
出版历程
- 收稿日期: 2016-01-19
- 修回日期: 2016-10-25
- 刊出日期: 2017-02-25

Dynamic characteristics analysis of refueling drogue at various docking velocities

Department of Aerodynamics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 采用CFD数值模拟的手段，模拟了飞机在不同对接速度下加油锥套的运动情况。空间离散采用了Osher格式，紊流模型采用了S-A一方程紊流模型，动网格采用了适合柔性变形的基于Delauney图的动网格技术，运用“刚杆-球铰”模型离散方法对软管锥套系统进行建模，建立了软管多体系统模型并得到其运动控制方程。计算结果表明，不同的对接速度对锥套的运动有较大的影响，低于3m/s时，锥套向上飘移并且伴有周期性摆动；当以3 m/s速度进行对接时，加油锥套存在向上移动，飘移距离在0.6 m左右，但周期性的振荡表现较小。本文的结果为该类飞机加油的对接速度提供参考。
- 空中加油 /
- 数值模拟 /
- 加油锥套 /
- 动网格 /
- 加油对接
Abstract: The CFD method was applied to solve the refueling docking at different docking velocities. The Osher scheme and S-A turbulence model were used to solve the compressible Navier-Stokes equations, and the Delaunay mapping dynamic grid method was employed the flexible deformation of the hose in the numerical implementation. The hose was discretized into a series of ball hinges linked by massless rigid links which form a multi-body the kinematical and dynamic equations were then derived for the system. All the numerical results show that the refueling docking velocity is very crucial for aerial refueling. When the docking velocity is lower than 3 m/s, the refueling drogue will move upward with obvious cycle staggering, compared with slight cycle staggering at the speed of 3m/s, which makes it much easier to refuel. Results of this study may have certain reference significance for the drogue-probe aerial refueling.
- aerial refueling /
- numerical simulations /
- refueling drogue /
- dynamic grid /
- refueling docking

HTML全文

图 1 加油软管网格移动前后示意图

Figure 1. Hose mesh before and after movement

下载: 全尺寸图片幻灯片

图 2 软管多体系统模型及坐标系描述

Figure 2. Demonstration for horse model and coordinates

下载: 全尺寸图片幻灯片

图 3 节点i受力分析

Figure 3. Force analysis for point i

下载: 全尺寸图片幻灯片

图 4 DLR-F4翼身组合体网格及极曲线

Figure 4. Mesh and polar curve for DLR-F4

下载: 全尺寸图片幻灯片

图 5 0.6m/s对接速度时加油锥套运动轨迹图

Figure 5. Trajectory path of drogue at 0.6m/s

下载: 全尺寸图片幻灯片

图 6 加油锥套模拟结果图

Figure 6. Simulation results for the refueling drogue

下载: 全尺寸图片幻灯片

图 7 1.2m/s对接速度时加油锥套运动轨迹图

Figure 7. Trajectory path of drogue at 1.2m/s

下载: 全尺寸图片幻灯片

图 8 2m/s对接速度时加油锥套运动轨迹图

Figure 8. Trajectory path of drogue at 2m/s

下载: 全尺寸图片幻灯片

图 9 3m/s对接速度时加油锥套运动轨迹图

Figure 9. Trajectory path of drogue at 3m/s

下载: 全尺寸图片幻灯片

图 10 飞机接近时流线及压力云图

Figure 10. Streamlines and pressure contours

下载: 全尺寸图片幻灯片

图 11 锥套平衡位置的移动情况

Figure 11. Variation of equilibrium position of drogue

下载: 全尺寸图片幻灯片

表 1 软管和锥套的参数及尺寸

Table 1. Parameters and sizes of hose and drogue

物理参数	软管总长 /m	杨氏模量 /MPa	软管线密度 /(kg·m^-1)	锥套质量 /kg	稳定伞阻尼面积 /m²
	24.0	8.0	4.2	30.0	0.204

下载: 导出CSV

参考文献(21)

[1]	徐干, 曹近齐.国外空中加油技术的现状及发展[J].航空科学技术, 1995, 1:27-30. Xü G, Cao J Q. The status and development of overseas in-flight refueling technology[J]. Aeronautical Science and Technology, 1995, 1:27-30. (in Chinese)
[2]	Vassberg J C, Yeh D T, Blair A J, et al. Dynamic characteristics of a KC-10 wing-pod refueling hose by numerical simulation[R]. AIAA 2002-2712.
[3]	Vassberg J C, Yeh D T, Blair A J, et al. Numerical simulation of KC-10 in-flight refueling hose-drogue dynamics with an approaching F/A-18D receiver aircraft[R]. AIAA 2005-4605.
[4]	Vassberg J C, Yeh D T, Blair A J, et al. Numerical simulations of KC-10 wing-mount aerial refueling hose-drogue dynamics with a reel take-up system[R]. AIAA 2003-3508.
[5]	Ribbens W B, Saggio F, Wierenga R, et al. Dynamic modeling of an aerial refueling hose & drogue system[R]. AIAA 2007-3802.
[6]	Ro K, Kamman J W. Modeling and simulation of hose-paradrogue aerial refueling systems[J]. Journal of Guidance, Control and Dynamics, 2010, 33(1):53-63. doi: 10.2514/1.45482
[7]	Venkataramanan S, Dogan A. Dynamic effects of trailing vortex with turbulence & time-varying inertia in aerial refueling[R]. AIAA 2004-4945.
[8]	Venkataramanan S, Dogan A. Modeling of aerodynamic coupling between aircraft in close proximities[R]. AIAA 2004-5172.
[9]	Venkataramanan S, Dogan A, Blake W. Vortex effect modeling in aircraft formation flight[R]. AIAA 2003-5385.
[10]	Eichler J. Dynamic analysis of an in-fIight refueling system[J]. Journal of Aircraft, 1978, 15(5):311-318. doi: 10.2514/3.58361
[11]	Hoerner S F. Fluid-dynamic drag[M]. Brick Town:Hoerner, 1965:454-455.
[12]	胡孟权, 柳平, 聂鑫, 等.大气紊流对空中加油软管锥套运动的影响[J].飞行力学, 2010, 28(5):20-23. http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201005006.htm Hu M Q, Liu P, Nie X, et al. Influence of air turbulence on the movement of hose-drogue[J]. Flight Dynamics, 2010, 28(5):20-23. (in Chinese) http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201005006.htm
[13]	王伟, 刘喜藏, 王鹏.空中加油对接过程软管-锥套动态特性[J].飞行力学, 2013, 31(2):180-183. http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201302021.htm Wang W, Liu X C, Wang P. Dynamics of hose-drogue refueling systems during coupling[J]. Flight Dynamics, 2013, 31(2):180-183. (in Chinese) http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201302021.htm
[14]	Dogan A, Lewis T A, Blake W. Flight data analysis and simulation of wind effects during aerial refueling[J]. Journal of Aircraft, 2008, 45(6):2036-2048. doi: 10.2514/1.36797
[15]	Dogan A, Blake W. Modeling of bow wave effect in aerial refueling[R]. AIAA 2010-7926.
[16]	Bhandari U, Thomas P R, Bullock S, et al. Bow wave effect in probe and drogue aerial refueling[R]. AIAA 2013-4695.
[17]	Spalart P R, Allmaras S R. A one-equation turbulence model for aerodynamic flows[R]. AIAA-92-0439, 1992.
[18]	Osher S, Solomon F. Upwind difference schemes for hyperbolic systems of conservation laws[J]. Mathematics of computation, 1982, 38(158):339-374. doi: 10.1090/S0025-5718-1982-0645656-0
[19]	Liu X Q, Qin N, Xia H. Fast dynamic grid deformation based on Delaunay graph mapping[J]. Journal of Computational Physics, 2006, 211(2):405-423. doi: 10.1016/j.jcp.2005.05.025
[20]	陈乐乐, 刘学强, 吴成林.稳定伞变阻尼过程动态特性研究[J].南京航空航天大学学报, 2015, 47(4):607-612. http://www.cnki.com.cn/Article/CJFDTOTAL-NJHK201504020.htm Chen L L, Liu X Q, Wu C L. Dynamic characteristics research for variable damping paradrogue, Journal of Nanjing University of Aeronautics & Astronautics, 2015, 47(4):607-612. (in Chinese) http://www.cnki.com.cn/Article/CJFDTOTAL-NJHK201504020.htm
[21]	Redeker G. DLR-F4 wing-body configuration, a selection of experimental test cases for the validation of CFD codes[R]. AGARD AR-303, 1994.