襟缝翼可动翼面的随动加载方法研究

庞宝才; 董登科; 弓云昭; 常文魁

doi:10.13433/j.cnki.1003-8728.2014.1029

襟缝翼可动翼面的随动加载方法研究

doi: 10.13433/j.cnki.1003-8728.2014.1029

1.
中航工业飞机强度研究所, 西安 710068

详细信息

作者简介:
庞宝才(1982-)，工程师，硕士研究生，研究方向为金属结构疲劳/可靠性，baocai9808@163.com;董登科(联系人)，副总师，博士，dengke623@sina.com

庞宝才(1982-)，工程师，硕士研究生，研究方向为金属结构疲劳/可靠性，baocai9808@163.com;董登科(联系人)，副总师，博士，dengke623@sina.com

计量
- 文章访问数: 153
- HTML全文浏览量: 28
- PDF下载量: 8
- 被引次数: 0
出版历程
- 收稿日期: 2013-04-04

Study on Tracking Loading Method of Locomotory Wing for Flap and Slat

1.
AVIC Aircraft Strength Research Institute, Xi'an 710068

摘要

摘要: 以襟缝翼运动机构作为研究对象,模拟飞机真实飞行状态。首先通过对机翼盒段模拟件的刚度施加,满足了襟缝翼的刚度支持条件;其次采用单点双作动筒随动加载方案,通过控制作动筒载荷施加的大小及方向,模拟完成了襟缝翼运动机构在起飞和着陆放、收襟缝翼时襟缝翼上的气动载荷的变化过程。试验结果显示:襟翼和缝翼的每个通道力载误差都小于5%,此种襟缝翼可动翼面随动加载方法是可行的、有效的。
- 襟缝翼 /
- 可动翼面 /
- 随动加载
Abstract: The object of the study is the flap and slat motion mechanism.For simulating the real aircraft flightcondition, firstly, it meted the boundary conditions for the flap and slat by pressurizing rigidly on the box specimenof wing; secondly, using the single-point dual-actuator loading scheme, the changes of aerodynamic loads on theflap and slat motion mechanism under launch and retrieval conditions during takeoff and landing were simulated, bycontrolling size and the direction of actuator applied load.The study result of the test and analysis shows: the errorof the flap and slat each channel wing loading is less than 5%.The tracking loading method of locomotory wing forflap and slat is feasible and effective.
- actuators /
- aerodynamic loads /
- aircraft

HTML全文

参考文献(8)

[1]	孙侠生，董登科，等.军用飞机结构耐久性/损伤容限分析和设计指南[M].2005Sun X S，Dong D K，et al.Military aircraft structuredurability damage tolerance analysis and design guide[M].2005 (in Chinese)
[2]	张晓辉，冯蕴雯，冯元生.基于可靠性的某型飞机襟翼刚度优化设计[J].机械科学与技术，2010，29 (8):1076-1080Zhang X H ，Feng Y W，Feng Y S.Stiffness optimizationdesign of the flap of an aircraft based on reliability [J].Mechanical Science and Technology for AerospaceEngineering,2010,29(8): 1076-1080 (in Chinese)
[3]	刘东岳，万志强，杨超，等.大展弦比机翼总体刚度的气动弹性优化设计[J].航空学报,2011,32(6)Liu D Y,Wan Z Q,Yang C,et al.Aeroelasticoptimization design method of global stiffness for highaspect ratio wing[J].Acta Aeronautica et AstronauticaSinica,2011,32(6) (in Chinese)
[4]	朱鲜飞，冯蕴雯，薛小峰.大展弦比复杂机翼刚度计算方法研究[J].机械科学与技术,2011,30(3): 473-478Zhu X F，Feng Y W，Xue X F.A calculation method forthe stiffness of complex wings with large aspect ratio[J].Mechanical Science and Technology for AerospaceEngineering,2011,30(3): 473-478 (in Chinese)
[5]	王飞，何景武.基于仿生学的机翼结构刚度和强度设计研究[J].飞机设计,2010,30(4): 1-4Wang F，He J W.Research into aerofoil structure rigidityand intensity design based on bionics [J].AircraftDesign,2010,30(4): 1-4 (in Chinese)
[6]	刘军.某型飞机后缘襟翼运动机构动力学仿真分析研究[J].科技创新导报,2011,33(3): 14-15Liu J.XX Aircraft trailing flap mechanisms dynamicssimulation analysis and research [J].Science andTechnology Innovation Herald，2011，33 (3): 14-15 (in Chinese)
[7]	邱亚松，白俊强，李亚林，等.复杂几何细节对增升装置气动性能影响研究[J].航空学报,2012,33(3): 421-429Qiu Y S，Bai J Q，Li Y L，et al.Study on influence ofcomplex geometry details on the aerodynamic performanceof high-lift system[J].Acta Aeronautica et Astronauticasinica,2012,33(3): 421-429 (in Chinese)
[8]	褚胡冰，张彬乾，陈迎春，等.微型后缘增升装置增升效率及几何参数影响研究[J].航空学报,2012,33(3): 381-389Chu H B，Zhang B Q，Chen Y C，et al.Investigation onmini-TED efficiency and impact of its geometricalparameters[J].Acta Aeronautica et Astronautica Sinica，2012,33(3): 381-389 (in Chinese)