商用飞机翼尖装置减阻机理及其发展与应用

doi:10.16080/j.issn1671-833x.2015.15.120

摘要
参考文献
相关文章 (4)

全文: PDF (1764 KB)
输出: BibTeX | EndNote (RIS)

摘要推导了商用飞机诱导阻力公式，给出经典的诱导阻力表达式。对翼尖装置发展和演变历史进行了梳理，分析了翼梢小翼的减阻机理。从端板作用、耗散翼尖涡等5个方面分析了翼梢小翼对商用飞机飞行性能的影响，在此基础上提出了翼梢小翼的设计参数和设计原则。最后研究了应用于不同型号商用飞机的翼梢小翼的特点和最新进展。研究结果表明，商用飞机使用翼梢小翼能够显著降低诱导阻力，增加升阻比并提高燃油经济性。同时，商用飞机翼梢小翼正向着智能变形结构方向发展，以实现不同飞行任务阶段的性能最优化。

	服务

	把本文推荐给朋友
	加入我的书架
	加入引用管理器
	E-mail Alert
	RSS
	作者相关文章
	仇翯辰
	邱志平
	陈贤佳
	郭京

关键词 ：商用飞机, 翼梢小翼, 诱导阻力, 设计参数, 可变形结构

基金资助:中航工业2012产学研项目（cxy2012BH07）；国防基础科研计划项目（A2120110001，B2120110011）；国家自然科学基（10872017,90816024,10876100）“111”计划项目（B07009）；中国商飞未来民机产品研究项目。

引用本文:

仇翯辰，邱志平，陈贤佳，郭京. 商用飞机翼尖装置减阻机理及其发展与应用[J]. 航空制造技术, 2015, 58(15): 120-125.

链接本文:

http://www.amte.net.cn/CN/10.16080/j.issn1671-833x.2015.15.120 或 http://www.amte.net.cn/CN/Y2015/V58/I15/120

[1] 孙贺亮.大型民用客机翼梢小翼气动设计研究[D].北京:北京航空航天大学机械工程及自动化学院, 2008.
[2] 江永泉. 飞机翼梢小翼设计. 北京:航空工业出版社, 2009.
[3] 司亮,王和平,龚翠翠.翼稍装置对机翼气动、结构特性影响研究.空气动力学学报,2011,29(2):177-179.
[4] 杜绵银,崔尔杰,陈培,等.一种新型商用飞机翼梢小翼设计及优化.飞机设计,2012,32(2):23-27.
[5] Takenaka K,Hatanaka K,Yamazaki W,et al. Multidisci-plinary design exploration for a winglet. Journal of Air-craft, 2008,45(5):1601-1611.
[6] Ameri N,Lowenberg M H,Friswell M I,et al. Modelling continuously morphing aircraft for flight control. 19th Interna-tional Conference on Adaptive Structures and Technology Ascona: AIAA, 2008.
[7] Gerontakos P,Lee T. Effects of winglet dihedral on a tip vortex. Journal of Aircraft,2006,43(1):117-124.
[8] Bourdin P, Gatto A, Friswell M I. Aircraft control via vari-able cant-angle winglet. Journal of Aircraft,2008,45(2):414-423.
[9] Reneaux J. Overview on drag reduction technologies for civil transport aircraft. ECCOMAS, 2004.
[10] 钱翼稷. 空气动力学.北京:北京航空航天大学出版社, 2004.
[11] 李伟.变高度、变倾角的翼梢小翼驱动技术研究[D]南京:南京航空航天大学, 2012.
[12] Falcao L,Gomes A A,Suleman A. Aero-structure design optimation of a morphing wingtip. Journal of Intelligent Ma-terial Systems and Structures, 2011, 22(10):1112-1126.
[13] Ursache N M,Melin T,Isikveren A T,et al. Technology integration for active poly-morphing winglets development. ASME Conference on Smart Materials,Adaptive Structures and Intelligent Systems Ellicott City:ASME,2008.
[14] 江永泉. 翼梢小翼的空气动力机理. 民用飞机设计与研究,1993(3):16-22.
[15] Maughmer M D. Design of winglets for high-performance sailplanes. Journal of Aircraft, 2003, 40(6):1099-1106.
[16] Ishimitsu K K. Design and analysis of winglets for military aircraft. AFFDL-TR-76-6,1976.
[17] Conley N. Winglet toe-out angle optimization for the gates Learjet longhorn wing. Journal of Aircraft, 1980,17(12):851-855.
[18] Sankrithi M M K V, Frommer J B. Controllable winglets, USA, A1, US 2008/0308683, 2008.
[19] Hoisington Z C, Rawdon B K. Ground effect wing having a variable sweep winglet, USA, B1, US 6547181, 2003.
[20] DANG IA P K, PALMER M E, DOE R H. Aerodynamic design studies of conventional & unconventional wings with winglets. AIAA, 2006-3460.
[21] MATTOS S De, et al. Considerations about winglet design. AIAA, 2003-3502.
[22] 党铁红.民用飞机翼梢小翼的设计研究. 民用飞机设计与研究, 2003, 4:13-16.
[23] Krzysztof K. Wing-winglet design methodology for low speed applications. AIAA 2003-215, 2003.
[24] 汤坚玉,刘忠,陈丹军. 波音新一代民机战略分析.国际航空, 2012, 9:40-42.
[25] Catalano F M,Ceron-Munoz H D. Experimental analysis of the aerodynamic characteristics of adaptive multi-winglets. 43rd AIAA, Aerospace Science Meeting and Exhibit, Reno: AIAA, 2005.
[26] Gatto A, Mattioni F, Friswell M I. Experimental investigation of bistable winglets to enhance wing lift takeoff capability. Journal of Aircraft, 2009, 46(2):647-655
[27] Ursache N M, Melin T, Isikveren A T, at al. Morphing winglets for aircraft mutli-phase improvement. 7th AIAA Avia-tion Technology, Integration and Operation Conference, Bel-fast: AIAA, 2007.
[28] Boller C, Kuo C M. Demonstration of adaptive structure performance on modular micro air vehicle. 51st AIAA/ASME/ASCE/AHS/ASC Structure, Structure Dy-namics, and Materials Conference, Orlando: AIAA, 2010.
[29] Allen J B . Articulating winglets, USA, A, US005988563, 1999.
[30] Fitzgibbon T F. Wing fold actuator system for aircraft. USA, A, US5310138, 1994.