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弹性前掠翼开裂式方向舵操纵特性分析

马斌麟 苏新兵 冯浩洋 王宁 张亚光

马斌麟, 苏新兵, 冯浩洋, 等 . 弹性前掠翼开裂式方向舵操纵特性分析[J]. 北京航空航天大学学报, 2017, 43(9): 1849-1858. doi: 10.13700/j.bh.1001-5965.2017.0142
引用本文: 马斌麟, 苏新兵, 冯浩洋, 等 . 弹性前掠翼开裂式方向舵操纵特性分析[J]. 北京航空航天大学学报, 2017, 43(9): 1849-1858. doi: 10.13700/j.bh.1001-5965.2017.0142
MA Binlin, SU Xinbing, FENG Haoyang, et al. Control characteristics analysis of split rudder of elastic forward swept wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(9): 1849-1858. doi: 10.13700/j.bh.1001-5965.2017.0142(in Chinese)
Citation: MA Binlin, SU Xinbing, FENG Haoyang, et al. Control characteristics analysis of split rudder of elastic forward swept wing[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(9): 1849-1858. doi: 10.13700/j.bh.1001-5965.2017.0142(in Chinese)

弹性前掠翼开裂式方向舵操纵特性分析

doi: 10.13700/j.bh.1001-5965.2017.0142
基金项目: 

国家自然科学基金 11402301

陕西省自然科学基础研究计划 2015JM1005

详细信息
    作者简介:

    马斌麟  男, 硕士研究生; 主要研究方向:飞行器设计及计算流体力学

    苏新兵  男, 博士, 副教授, 硕士生导师; 主要研究方向:飞行器设计及计算流体力学

    通讯作者:

    苏新兵, E-mail:sxinbing01@163.com

  • 中图分类号: V221.3

Control characteristics analysis of split rudder of elastic forward swept wing

Funds: 

National Natural Science Foundation of China 11402301

Natural Science Basic Research Plan in Shaanxi Province of China 2015JM1005

More Information
  • 摘要:

    针对机翼弹性变形对前掠翼(FSW)飞行器开裂式方向舵操纵特性的影响,基于计算流体力学/计算结构力学(CFD/CSD)松耦合静气动弹性数值计算方法,计算了亚声速条件下刚性和弹性前掠机翼开裂式方向舵的操纵特性,并分析了机翼弯扭变形对方向舵操纵特性的影响。计算结果表明,右侧开裂式方向舵打开后,与刚性翼相比,弹性翼的失速迎角提前约2°,达到最大升阻比的迎角提前约1°,小迎角时偏航作用增强,出现右滚力矩和滚转力矩"凹坑"现象,大迎角时偏航规律趋势提前约8°,滚转作用加剧;侧滑角增大时,偏航力矩减小的幅度大于刚性翼,滚转力矩完全反效;舵偏角增大时,偏航力矩的增幅小于刚性翼。经比较,在弹性变形影响下,弹性前掠翼的开裂式方向舵操纵特性与刚性前掠翼有明显区别。

     

  • 图 1  HIRENASD流场和结构网格

    Figure 1.  Flow field and structure grids of HIRENASD

    图 2  不同y/b时的压力系数

    Figure 2.  Pressure coefficient of different y/b

    图 3  前掠翼模型及舵偏角示意图

    Figure 3.  Schematic of FSW model and rudder deflection angle

    图 4  计算模型

    Figure 4.  Computational model

    图 5  前掠翼流场和结构网格

    Figure 5.  Flow field and structure grids of FSW

    图 6  升阻特性

    Figure 6.  Lift-drag characteristics

    图 7  机翼展向扭转角

    Figure 7.  Torsional angle of wing along spanwise direction

    图 8  机翼展向弯曲挠度

    Figure 8.  Bending deflection of wing along spanwise direction

    图 9  翼梢处扭转角响应

    Figure 9.  Response of torsional angle of wing tip

    图 10  压力云图

    Figure 10.  Pressure contour

    图 11  偏航力矩特性

    Figure 11.  Yawing moment characteristics

    图 12  滚转力矩特性

    Figure 12.  Rolling moment characteristics

    图 13  升力系数

    Figure 13.  Lift coefficient

    图 14  侧滑偏航特性

    Figure 14.  Side slip yawing characteristics

    图 15  侧滑时的展向扭转角

    Figure 15.  Torsional angle with side slip along spanwise direction

    图 16  侧滑滚转特性

    Figure 16.  Side slip rolling characteristics

    图 17  偏航力矩系数增量及偏航操纵效率随舵偏角的变化

    Figure 17.  Variation of increment of yawing moment coefficient and yaw control efficiency with rudder deflection angle

    图 18  滚转力矩系数随舵偏角的变化

    Figure 18.  Variation of rolling moment coefficient with rudder deflection angle

    表  1  前掠翼飞行器的典型飞行状态

    Table  1.   Typical flight state of FSW aircraft

    飞行状态 H/km Ma
    起飞 0 0.2
    巡航 10 0.8
    空战 5 0.5
    下载: 导出CSV

    表  2  前掠翼阻力系数增量

    Table  2.   Increment of drag coefficient for FSW

    δ/(°) ΔCD/%
    刚性翼 弹性翼
    10 10.20 7.55
    20 23.64 19.89
    30 41.43 35.18
    下载: 导出CSV
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出版历程
  • 收稿日期:  2017-03-13
  • 录用日期:  2017-05-24
  • 网络出版日期:  2017-09-20

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