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超高速飞行器平尾大迎角气动弹性特性研究

郝帅 马铁林 王一 张子伦 罗文莉 向锦武

郝帅, 马铁林, 王一, 等 . 超高速飞行器平尾大迎角气动弹性特性研究[J]. 北京航空航天大学学报, 2021, 47(5): 983-993. doi: 10.13700/j.bh.1001-5965.2020.0089
引用本文: 郝帅, 马铁林, 王一, 等 . 超高速飞行器平尾大迎角气动弹性特性研究[J]. 北京航空航天大学学报, 2021, 47(5): 983-993. doi: 10.13700/j.bh.1001-5965.2020.0089
HAO Shuai, MA Tielin, WANG Yi, et al. Aeroelastic characteristics of hypersonic vehicle tail at high angle of attack[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(5): 983-993. doi: 10.13700/j.bh.1001-5965.2020.0089(in Chinese)
Citation: HAO Shuai, MA Tielin, WANG Yi, et al. Aeroelastic characteristics of hypersonic vehicle tail at high angle of attack[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(5): 983-993. doi: 10.13700/j.bh.1001-5965.2020.0089(in Chinese)

超高速飞行器平尾大迎角气动弹性特性研究

doi: 10.13700/j.bh.1001-5965.2020.0089
基金项目: 

国家自然科学基金 91216102

详细信息
    作者简介:

    郝帅  男, 博士研究生。主要研究方向: 飞行器总体设计、流固耦合技术、多学科优化技术

    马铁林  男, 博士, 研究员, 博士生导师。主要研究方向: 飞行器总体设计、无人机技术、多学科优化技术

    王一  男, 硕士研究生。主要研究方向: 飞行器总体设计、多学科优化技术

    通讯作者:

    马铁林, E-mail: matielin@buaa.edu.cn

  • 中图分类号: V215.3

Aeroelastic characteristics of hypersonic vehicle tail at high angle of attack

Funds: 

National Natural Science Foundation of China 91216102

More Information
  • 摘要:

    临近空间超高速飞行器在飞行过程中受到外部干扰作用时会出现大迎角飞行姿态,此时需大角度偏转全动平尾进行配平,带来平尾大迎角下的气动弹性问题。采用计算流体力学/计算固体力学/计算热力学(CFD/CSD/CTD)耦合方法分析了一种超高速飞行器全动平尾的气动弹性特性,重点研究了大迎角下平尾的气动响应及结构变形特点。结果表明:各迎角时的气动力曲线均出现波动,随时间变化逐渐衰减至平衡位置。迎角越大,初始振幅越大,气动力系数减小的比例越大,但随时间衰减得越快。平尾存在弯曲/扭转耦合现象,结构变形导致表面压力分布发生变化,使得整体压力减小、升力系数降低,迎角越大现象越明显。平尾最大应力在迎角30°时达1.2 GPa,已达到所用镍合金材料的屈服强度极限。应在结构设计时在翼轴与平尾接触部位附近加强,或在控制方案设计时限制全动平尾的工作角度。结构发生轴向与法向变形,轴向变形主要由气动热引起,法向变形由气动力和气动热共同引起。

     

  • 图 1  全动尾翼模型

    Figure 1.  Model of all-movable tail

    图 2  转轴形式

    Figure 2.  Form of rotating shaft

    图 3  尾翼/翼轴系统

    Figure 3.  System of tail/rotating shaft

    图 4  预估-校正迭代方法

    Figure 4.  Prediction-correction iterative method

    图 5  计算网格

    Figure 5.  Computational grid

    图 6  表面压力分布对比

    Figure 6.  Comparison of surface pressure distribution

    图 7  表面热流分布对比

    Figure 7.  Comparison of surface heat flux distribution

    图 8  不同迎角下气动力响应曲线

    Figure 8.  Aerodynamic response curves at different angles of attack

    图 9  表面压力系数分布云图

    Figure 9.  Distribution contour of surface pressure coefficients

    图 10  下表面压力系数分布曲线

    Figure 10.  Distribution curves lower surface pressure coefficients

    图 11  流场压力分布正视图和后视图

    Figure 11.  Front and back view of pressure distribution in flow field

    图 12  尾翼结构变形和压力分布云图

    Figure 12.  Structure deformation and pressure distribution contour of tail

    图 13  结构应力分布云图

    Figure 13.  Structural stress distribution contour

    图 14  10°迎角位移随时间变化曲线

    Figure 14.  Displacement curves at 10° angle of attack over time

    图 15  不同迎角下rArC随时间变化曲线

    Figure 15.  Curves of rA and rC at different angles of attack over time

    图 16  A点温度和热流变化曲线

    Figure 16.  Temperature and heat flux curves of point A

    图 17  40°迎角温度分布云图

    Figure 17.  Temperature distribution contour at 40° angle of attack

    图 18  结构轴向变形

    Figure 18.  Structure deformation along shaft direction

    图 19  结构法向变形

    Figure 19.  Structure deformation along normal direction

    表  1  全动尾翼几何参数

    Table  1.   Geometric parameters of all-movable tail

    参数 数值
    翼根弦长/m 0.63
    展长/m 0.22
    相对厚度 0.04
    面积/m2 0.15
    下载: 导出CSV

    表  2  钛合金材料参数

    Table  2.   Parameters of titanium alloy material

    参数 数值
    密度ρ/(kg·m-3) 4 400
    弹性模量E/GPa 75~109
    泊松比λ 0.34
    热膨胀系数α/(10-6 K-1) 9.2~11.0
    热导率k/(W·(m·K)-1) 6.8~11.8
    比热C/(J·(kg·K)-1) 610~702
    下载: 导出CSV

    表  3  镍合金材料参数

    Table  3.   Parameters of nickel alloy material

    参数 数值
    ρ/(kg·m-3) 8 240
    E/GPa 160~205
    λ 0.30
    α/(10-6 K-1) 11.8~18.7
    k/(W·(m·K)-1) 13.4~30.4
    C/(J·(kg·K)-1) 481~707
    下载: 导出CSV

    表  4  等效弹性常数

    Table  4.   Equivalent elastic constants

    参数 数值
    ρ/(kg·m-3) 924
    Ex/MPa 850~1 353
    Ey/MPa 605~963
    Ez/MPa 1 984~3 157
    α/(10-6 K-1) 13.3~18.6
    k/(W·(m·K)-1) 14.2~32.7
    C/(J·(kg·K)-1) 493~742
    λ 0.3
    下载: 导出CSV

    表  5  不同迎角下气动力响应

    Table  5.   Aerodynamic response at different angles of attack

    迎角/(°) CL减小量/% CD减小量/% 波动半衰期/s
    10 1 1 0.97
    20 3.6 4.7 0.73
    30 4.1 4.9 0.60
    40 5.1 6.6 0.48
    下载: 导出CSV
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出版历程
  • 收稿日期:  2020-03-10
  • 录用日期:  2020-05-30
  • 网络出版日期:  2021-05-20

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