考虑静气弹效应的大展弦比机翼舵面效率研究
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- 英文论文题名：Numerical Research on Control Surface Efficiency of Large-aspectratio Wing Considering Static Aeroelastic Effect
- 论文作者：张强 ; 周洲
- 英文论文作者：Zhang Qiang ; Zhou Zhou ; Beijing Aerospace Technology Institute ; College of Aeronautics ; NWPU
- 年：2016
- 作者机构：北京空天技术研究所;西北工业大学航空学院;
- 论文关键词：松耦合 ; 静气弹 ; 扭转变形 ; 舵面效率 ; 操纵反效 ; 弯扭耦合
- 英文论文关键词：loosely couple ; static aeroelastic ; twist ; control surface efficiency ; control reversal ; bending-torsional coupling
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（上册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：V211.41
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：7
- 文件大小：1951k
- 原文格式：O
- 会议级别：全国
摘要
采用松耦合方式,耦合计算流体力学和计算结构动力学,对考虑静气弹效应的机翼舵面效率包括平直翼和后掠翼两种构型进行了计算分析,并研究了静气弹效应导致机翼舵效降低的成因。结果表明:静气弹变形后,平直翼沿展向发生负扭转变形,并且随来流动压的增加,负扭转变形量增大,舵面效率的损失也随之增大;与平直翼相比,后掠翼由于存在弯扭耦合,舵效损失更为严重,在来流动压较大时甚至出现操纵反效。基于舵效损失成因的分析,通过增加后掠翼的弯曲刚度,改善了静气弹效应对舵面效率的不良影响。
By coupling CFD and CSD and using loosely-coupled algorithm,the control surface efficiency under considering static aeroelastic effect is numerically investigated,including straight and back-swept wing configuration,and the cause way static aeroelastic effect leads to the loss of control surface efficiency is studied.The results show that the straight wing twists negatively in spanwise direction after static aeroelastic deformation and twist deformation becomes larger with the dynamic pressure of free stream increasing.As a result,the loss of control surface efficiency becomes more serious.Compared to straight wing,back-swept wing is more serious because of bending-torsional coupling and control reversal will emerge when the dynamic pressure of free stream is comparatively large.Based on the analysis of the efficiency loss,the bad influence of aeroelastic effect is suppressed by increasing the bending stiffness of back-swept wing.
By coupling CFD and CSD and using loosely-coupled algorithm,the control surface efficiency under considering static aeroelastic effect is numerically investigated,including straight and back-swept wing configuration,and the cause way static aeroelastic effect leads to the loss of control surface efficiency is studied.The results show that the straight wing twists negatively in spanwise direction after static aeroelastic deformation and twist deformation becomes larger with the dynamic pressure of free stream increasing.As a result,the loss of control surface efficiency becomes more serious.Compared to straight wing,back-swept wing is more serious because of bending-torsional coupling and control reversal will emerge when the dynamic pressure of free stream is comparatively large.Based on the analysis of the efficiency loss,the bad influence of aeroelastic effect is suppressed by increasing the bending stiffness of back-swept wing.
引文
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[2]Farhat C,Pierson K,Degand C.CFD Based Simulation of the Unsteady Aeroelastic Response of a Maneuvering Vehicle[R].AIAA,2000-0899,2000.
[3]Palacios R,Cesnik C E S.Static Nonlinear Aeroelasticity of Flexible Slender Wings in Compressible Flow[R].AIAA,2005-1945,2005.
[4]Attar P J,Gordnier R E.Aeroelastic Prediction of the Limit Cycle Oscillations of a Cropped Delta wing[J].Journal of Fluids and Structures,2006,22:45-58.
[5]Andersen G,Kolonay R,Eastep F.Control-Surface Reversal in the Transonic Regime[J].Journal of Aircraft,1998,35(5):688-694.
[6]Kamakoti R,Shyy W.Fluid-Structure Interaction for Aeroelastic Applications[J].Progress in Aerospace Sciences,2004,40:535-558.