民机微型后缘开裂襟翼驱动机构设计及运动仿真分析
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摘要
民机的飞行速度变化范围大,高效增升装置是改善起飞/着陆等阶段低速性能的关键技术。以Y7飞机后缘后退双开缝襟翼为设计基础,设计了一套齿轮系加平行四边形机构的驱动机构,利用原有后缘襟翼收放动力,驱动后段襟翼上加装的微型开裂襟翼收放展开。通过收放运动过程仿真可知,微型襟翼随后缘襟翼展开的同步性达到了设计要求,从而保证放下后缘襟翼时机翼升力进一步同步增加。该研究对后期微型襟翼在各型民机上的加改装实施具有一定的参考价值。
The flight speed of civil aircraft has a wide range,so the high efficiency high-lift device is the key technique which improves the low speed performance of aircraft when it is landing or taking-off.Based on Y7 trailing edge backward dual-slot flap,a driving mechanism including gear set and parallelogram mechanism has designed.The mini-trailing edge split flap on aft flap is driven by the mechanism using the retraction-extension force of aft flap.By the retraction-extension motion simulation,the motion synchronicity of mini flap and aft flap has reached the requirements,so the lift of wing will further increase proportionately with the moving of trailing edge flap.The results would provide reference for the modification and adding of mini-trailing edge split flap on civil aircraft.
The flight speed of civil aircraft has a wide range,so the high efficiency high-lift device is the key technique which improves the low speed performance of aircraft when it is landing or taking-off.Based on Y7 trailing edge backward dual-slot flap,a driving mechanism including gear set and parallelogram mechanism has designed.The mini-trailing edge split flap on aft flap is driven by the mechanism using the retraction-extension force of aft flap.By the retraction-extension motion simulation,the motion synchronicity of mini flap and aft flap has reached the requirements,so the lift of wing will further increase proportionately with the moving of trailing edge flap.The results would provide reference for the modification and adding of mini-trailing edge split flap on civil aircraft.
引文
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[4]Zhu S S,Qiu Y.Studies in Application of Zhu's Flap to High Lift System for Aircrafts[C].San Francisco:AIAA Atmospheric Flight Mechanics Conference and Exhibit,2005:2005-6338.
[5]Melton L T P,Yao C S,Seifert A.Application of excitation from multiple locations on a simplified high-lift system[C].2nd AIAA Flow Control Conference,2004:2004-2324.
[6]Singh M K,Dhanalakshmi K,Chakrabartty S K.Navier-Stokes Analysis of Airfoils with Gurney Flap[J].Journal of Aircraft,2007,44(5):1487-1493.
[7]周涛,李亚林,陈迎春.增升装置中的流动控制技术[J].上海交通大学学报,2014,48(2):214-221.
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