|Table of Contents|

Safety analysis of aircraft encountering wake vortex(PDF)

《交通运输工程学报》[ISSN:1671-1637/CN:61-1369/U]

Issue:
2012年01期
Page:
45-49
Research Field:
载运工具运用工程
Publishing date:

Info

Title:
Safety analysis of aircraft encountering wake vortex
Author(s):
HAN Hong-rong1; LI Na2; WEI Zhi-qiang1
1.School of Air Traffic Management,Civil Aviation University of China,Tianjin 300300,China; 2.China Academy of Civil Aviation Science and Technology,Beijing 100028,China
Keywords:
flight safety;  wake vortex;  stall speed;  wake vortex field;  rolling bank angle
PACS:
V328
DOI:
-
Abstract:
The response mechanism of aircraft encountering wake vortex was analyzed,and the calculation model of induced moment was developed.The calculating model of aircraft’s rolling parameters was constructed based on considering of the damping characteristics of aircraft,the response times,the handling qualities and so on.The calculation model of the accepted maximum bank angle was constructed based on the assumption that the buffet stall speed was posed as a critical limit in calculating the rolling progress.The rolling parameters and safe intervals of wake vortex under certain wake vortex’s field condition were calculated by using Delphi7.0.The influences of aircraft mass,speed,altitude tolerance and initial bank angle on flight safety were analyzed.Research result shows that at a certain speed,the greater aircraft mass is,the smaller the accepted maximum bank angle is.The safe interval of aircraft with certain mass decreases with the increase of speed and the decrease of altitude tolerance,while it increases with the increase of initial bank angle.Comparing the data calculated by the models with ICAO standard data,the maximal deviation is 1.56%,which verifies the correctness of the computation method.

References:

[1] 魏志强,徐肖豪.飞机尾涡流场的建模与仿真计算研究[J].交通运输系统工程与信息,2010,10(4):186-191. WEI Zhi-qiang, XU Xiao-hao. Modeling and simulating of flow field for aircraft wake vortex[J]. Journal of Transportation Systems Engineering and Information Technology, 2010, 10(4): 186-191.(in Chinese)
[2] VICROY D D, VIJGEN P M, REIMER H M, et al. Recent NASA wake-vortex flight tests, flow-physics database and wake-development analysis[C]∥AIAA. World Aviation Congress and Exposition. Anaheim: AIAA, 1998: 1-14.
[3] LIOT D. Wake vortex encounter model implementation and validation in the online(piloted)flight simulation environment[R]. Toulouse: WAVENC Technical Note TN-19, AM Airbus, 2000.
[4] DE BRUIN A C, SPEIJKER L J P, MOET H, et al. S-wake: assessment of wake vortex safety[R]. Amsterdam: National Aerospace Laboratory NLR, 2003.
[5] LUCKNER R, HÖHNE G, FUHRMANN M. Hazard criteria for wake vortex encounters during approach[J]. Aerospace Science and Technology, 2004, 8(8): 673-687.
[6] BRANDON J M, JORDAN F L, STUEVER R A, et al. Application of wind tunnel free-flight technique for wake vortex encounters[R]. Washington DC: NASA, 1997.
[7] PADFIELD G D, MANIMALA B, TURNER G P. A severity analysis for rotorcraft encounters with vortex wakes[J]. Journal of the American Helicopter Society, 2004, 49(4): 445-456.
[8] LAWRENCE B, PADFIELD G D. Wake vortex encounter severity for rotorcraft in approach and landing[R]. Florence: 31st European Rotorcraft Forum, 2005.
[9] 胡 军,徐肖豪.空中交通中尾流间隔的研究[J].中国民航学院学报,2002,20(4):1-5. HU Jun, XU Xiao-hao. Wake vortex separation of ATC[J]. Journal of Civil Aviation University of China, 2002, 20(4): 1-5.(in Chinese)
[10] 冯志勇.尾流对飞行的影响及安全间隔研究[D].成都:西南交通大学,2007. FENG Zhi-yong. How wake vortexes affect the flights and safety separation research[D]. Chengdu: Southwest Jiaotong University, 2007.(in Chinese)
[11] 徐肖豪,赵鸿盛,杨传森,等.飞行进近中尾流的大涡数值模拟[J].南京航空航天大学学报,2010,42(2):179-184. XU Xiao-hao, ZHAO Hong-sheng, YANG Chuan-sen, et al. Large eddy simulation of wake vortex during approach[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2010, 42(2): 179-184.(in Chinese)
[12] 徐肖豪,赵鸿盛,王振宇.尾流间隔缩减技术综述[J].航空学报,2010,31(4):655-662. XU Xiao-hao, ZHAO Hong-sheng, WANG Zhen-yu. Overview of wake vortex separation reduction systems[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(4): 655-662.(in Chinese)
[13] POIREL D, PRICE S J. Bifurcation characteristics of a two-dimensional structurally non-linear airfoil in turbulent flow[J]. Nonlinear Dynamics, 2007, 48(4): 423-435.
[14] BROWN A. The impact upon aircraft airworthiness design from encounters with discrete vortices[C]∥AIAA. 44th AIAA Aerospace Sciences Meeting and Exhibit. Reno: AIAA, 2006: 1-19.
[15] CROW S C. Stability theory for a pair of trailing vortices[J]. AIAA Journal, 1970, 8(12): 2172-2179.

Memo

Memo:
-
Last Update: 2012-02-28