流体力学与飞行力学

混合翼身布局客机SAX-40水上迫降力学性能数值研究

  • 郭保东 ,
  • 屈秋林 ,
  • 刘沛清 ,
  • 周志杰 ,
  • 张纯
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  • 1. 北京航空航天大学 航空科学与工程学院, 北京 100191;
    2. 北京航空航天大学 大型飞机高级人才培训班, 北京 100191
郭保东 男,博士研究生。主要研究方向:民用飞机水上迫降力学性能和水上飞机起飞降落性能等。 Tel:010-82315463 E-mail:gbd@ase.buaa.edu.cn;屈秋林 男,博士,讲师。主要研究方向:地面效应空气动力学、民用飞机水上迫降力学性能以及水上飞机起飞降落性能等。 Tel:010-82339592 E-mail:qql@buaa.edu.cn;刘沛清 男,博士,教授,博士生导师。主要研究方向:螺旋桨气动设计、漩涡分离流与流动控制、高速层流控制技术以及大型飞机起飞着陆气动性能。 Tel:010-82338967 E-mail:lpq@buaa.edu.cn

收稿日期: 2012-12-06

  修回日期: 2013-03-19

  网络出版日期: 2013-04-11

基金资助

航空科学基金(20102351023);高等学校博士学科点专项科研基金(20091102120021);国家"973"计划(2009CB72400101)

Ditching Performance of Silent Aircraft SAX-40 in Hybrid Wing-body Configuration

  • GUO Baodong ,
  • QU Qiulin ,
  • LIU Peiqing ,
  • ZHOU Zhijie ,
  • ZHANG Chun
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  • 1. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;
    2. Large Aircraft Advanced Training Centre, Beihang University, Beijing 100191, China

Received date: 2012-12-06

  Revised date: 2013-03-19

  Online published: 2013-04-11

Supported by

Aeronautical Science Foundation of China (20102351023);Research Fund for the Doctoral Program of Higher Education of China (20091102120021);National Basic Research Program of China (2009CB72400101)

摘要

为了验证未来混合翼身布局飞机的水上迫降力学性能,数值求解非定常雷诺时均Navier-Stokes (URANS)方程和Realizable κ-ε湍流模型,采用动网格方法处理飞机与水面间的相对运动、流体体积(VOF)模型追踪水面变形,模拟了SAX-40飞机刚性模型以12°初始俯仰角在平静水面上迫降的过程。结果分析表明:迫降过程中,触水时的冲击作用导致飞机下表面水线附近产生较大的正压峰值,入水后的浸没滑行作用导致机身下表面尾部弯曲部分出现大面积的负压,使得飞机发生大幅抬头;迫降过程中飞机的法向载荷峰值为2.87G,纵向载荷峰值为1.05G,表面冲击压力峰值为720 kPa。SAX-40飞机在水上迫降过程中有跳离水面的不稳定运动趋势,进行混合翼身布局设计时应予考虑。

本文引用格式

郭保东 , 屈秋林 , 刘沛清 , 周志杰 , 张纯 . 混合翼身布局客机SAX-40水上迫降力学性能数值研究[J]. 航空学报, 2013 , 34(11) : 2443 -2451 . DOI: 10.7527/S1000-6893.2013.0179

Abstract

The planned ditching of aircraft SAX-40 on calm water is numerically simulated to investigate the ditching performance of the hybrid wing-body configuration. The unsteady Reynolds-averaged Navier-Stokes (URANS) equations and the Realizable κ-ε turbulence model are solved by a fluent solver. The relative motion between the aircraft and water is handled by the dynamic mesh method. The air-water interface is tracked by a volume of fluid (VOF) model. During the ditching process, the impact brings about the positive pressure peak on the aircraft's lower surface near the waterline; and the planing brings forth the negative pressure on the aft curved portion of the aircraft's lower surface, resulting in a suck force and a strong nose-up pitch motion. As the aircraft touches the water, the normal load increases rapidly to 2.87G, and the longitudinal load to 1.05G. The slamming pressure reaches a peak of about 720 kPa. This airplane bounces up from the water and this defective performance should be considered during the design of a hybrid wing-body configuration.

参考文献

[1] Guo B D,Liu P Q,Cheng L.Airworthiness substantiation methods for civil transport ditching.Journal of Civil Aviation University of China,2008,26(S): 47-49.(in Chinese) 郭保东,刘沛清,程丽.民用飞机水上迫降适航验证技术概述.中国民航大学学报,2008,26(S): 47-49.

[2] Thompson W C.Model ditching investigation of the Boeing 707 jet transport.NACA Research Memorandum RM-SL55K08.Washington: National Advisory Committee for Aeronautics,1955.

[3] Thompson W C.Rough-water ditching investigation of a model of a jet transport with the landing gear extended and with various ditching aids.NASA Technical Note TN-D101 (NACA-TN-3775).Washington: National Aeronautics and Space Administration,1959.

[4] Thompson W C.Model ditching investigation of a jet transport airplane with various engine installations.NACA Research Memorandum L56G10.Washington: National Advisory Committee for Aeronautics,1956.

[5] Wang Y H.How to determine the performance of the aircraft ditching.International Aviation,1989,11: 61.(in Chinese) 王雨和.如何确定飞机水上迫降性能.国际航空,1989,11: 61.

[6] National Transportation Safety Board.Loss of thrust in both engines after encountering a flock of birds and subsequent ditching on the Hudson River,US Airways Flight 1549 Airbus A320-214.Aircraft Accident Report NTSB/AAR-10/03.2010-05-04.(http://www.ntsb.gov/Publictn/2010/AAR1003.htm)

[7] Fisher L J,Hoffman E L.Ditching investigations of dynamic models and effects of design parameters on ditching characteristics.NACA Report 1347,Langley Field VA: Langley Aeronautical Laboratory,National Advisory Committee for Aeronautics,1956.

[8] Smith A G,Warren C H E,Wright D F.Investigations of the behavior of aircraft when making a forced landing on water (ditching).Aeronautical Research Council Reports and Memoranda No.2917 (15040).London: Aeronautical Research Council,Her Majesty's Stationery Office,1957.

[9] Streckwall H,Lindenau O,Bensch L.Aircraft ditching: a free surface/free motion problem.Achieves of Civil and Mechanical Engineering,2007,7(3): 177-190.

[10] Wick A T,Zink G A.Computational simulation of an unmanned air vehicle impacting water.AIAA-2007-70,2007.

[11] Wittlin G,Smith M,Richards M.Airframe water impact analysis using a combined MSC-Dytran and DRI-Krash approach.The American Helicopter Society:The American Helicopter Society 53rd Annual Forum.Virginia: Curran Associates,Inc.,1997: 1-13.

[12] Climent H,Benitez L,Rosich F,et al.Aircraft ditching numerical simulation.Grant I: 25th International Congress of the Aeronautical Sciences.Hamburg: Optimage Ltd.2006: 1-16.

[13] Toso N R S.Contribution to the modelling and simulation of aircraft structures impacting on water.Stuttgart: Institute of Aircraft Design,University Stuttgart,2009.

[14] Guo B D,Liu P Q,Qu Q L.Effect of pitch angle on the initial stage of a transport aircraft ditching.Chinese Journal of Aeronautics,2013,26(1): 17-26.

[15] Leigh B R.Using the momentum method to estimate aircraft ditching loads.Canadian Aeronautics and Space Journal,1988,34(3): 162-169.

[16] Bensch L,Shigunov V,Soding H.Computational method to simulate planned ditching of a transport aircraft.Computational Fluid and Solid Mechanics,2003: 1251-1254.

[17] Hileman J I,Spakovszky Z S,Drela M.Airframe design for "silent aircraft".AIAA-2007-453,2007.

[18] Zhu Z Q,Wang X L,Wu Z C,et al.Discussion of design methods for silent and fuel efficient medium range civil transport.Acta Aeronautica et Astronautica Sinica,2008,29(3): 562-572.(in Chinese) 朱自强,王晓璐,吴宗成,等.高经济性静音中航程民机设计方法讨论.航空学报,2008,29(3): 562-572.

[19] Cheng H,Chao F.Simulation of fluid-solid interaction on water ditching of an airplane by ALE method.Journal of Hydrodynamics,2011,23(5): 637-642.

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