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固定鸭舵双旋弹全弹道动态稳定性及其影响因素

赵新新 史金光 王中原 张宁

赵新新, 史金光, 王中原, 张宁. 固定鸭舵双旋弹全弹道动态稳定性及其影响因素. 力学学报, 2022, 54(5): 1364-1374 doi: 10.6052/0459-1879-21-636
引用本文: 赵新新, 史金光, 王中原, 张宁. 固定鸭舵双旋弹全弹道动态稳定性及其影响因素. 力学学报, 2022, 54(5): 1364-1374 doi: 10.6052/0459-1879-21-636
Zhao Xinxin, Shi Jinguang, Wang Zhongyuan, Zhang Ning. Dynamic stability and influence factors of the whole trajectory of fixed canard dual-spin projectiles. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1364-1374 doi: 10.6052/0459-1879-21-636
Citation: Zhao Xinxin, Shi Jinguang, Wang Zhongyuan, Zhang Ning. Dynamic stability and influence factors of the whole trajectory of fixed canard dual-spin projectiles. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(5): 1364-1374 doi: 10.6052/0459-1879-21-636

固定鸭舵双旋弹全弹道动态稳定性及其影响因素

doi: 10.6052/0459-1879-21-636
基金项目: 国防预先研究资助项目(3020802010302)
详细信息
    作者简介:

    赵新新, 研究生, 主要研究方向: 外弹道理论与仿真. E-mail: 1607203853@qq.com

    史金光, 研究员, 主要研究方向: 弹箭飞行动力学与控制. E-mail: shijg1122@163.com

  • 中图分类号: TJ012.3

DYNAMIC STABILITY AND INFLUENCE FACTORS OF THE WHOLE TRAJECTORY OF FIXED CANARD DUAL-SPIN PROJECTILES

  • 摘要: 为研究固定鸭舵双旋弹全弹道飞行时的动态稳定性问题, 在小攻角条件下建立复攻角运动的状态空间模型, 并应用霍尔维茨方法导出其特征根实部皆负的一般性条件. 针对起控前/后前体滚转角的运动特点, 利用常规旋转弹的稳定性分析方法, 建立固定鸭舵双旋弹在不同飞行状态下的动态稳定性判据, 其与常规旋转弹的形式相似, 无控飞行时在升力和静力矩项中对应增加了舵面控制力和力矩项; 有控飞行时进一步增加了有关项相对增量的影响. 据此在后体参数确定的条件下推导舵面参数约束条件, 并分析操纵舵控制力系数导数、安装位置和舵偏角对动态稳定性的影响, 揭示了该类炮弹动不稳定形成的原因. 对复攻角运动在不同条件下的仿真分析结果表明, 当舵面引起的有关项相对增量同时位于无控和有控飞行的边界曲线内时, 固定鸭舵双旋弹全弹道飞行动态稳定, 验证了本文推导的动态稳定性判据和舵面参数约束条件合理, 为该类炮弹的研制提供了理论依据与设计参考.

     

  • 图  1  固定鸭舵双旋弹结构示意图

    Figure  1.  The configuration of the fixed canard dual-spin projectile

    图  2  动态稳定边界图

    Figure  2.  Dynamic stable boundary

    图  3  原弹的稳定因子

    Figure  3.  The stability factors of the original projectile

    图  4  操纵舵的控制力系数导数

    Figure  4.  Derivative of control force coefficient on control canard

    图  5  H ~ R相对增量边界曲线(t = 10 s)

    Figure  5.  H-R relative incremental boundary (t = 10 s)

    图  6  H ~ R相对增量边界曲线(t = 90 s)

    Figure  6.  H-R relative incremental boundary (t = 90 s)

    图  7  无控飞行时复攻角的幅值变化曲线

    Figure  7.  Amplitude of complex attack angle in uncontrolled flight

    图  8  T ~ R相对增量边界曲线(t = 90 s)

    Figure  8.  T-R relative incremental boundary (t = 90 s)

    图  9  不同控制方位下的复攻角运动曲线

    Figure  9.  Complex attack angle motion under different control directions

    图  10  控制方位多次切换的复攻角运动曲线

    Figure  10.  Complex attack angle motion with multiple switching of control directions

    表  1  弹丸物理参数

    Table  1.   Physical parameters of projectile

    m/kgl/mC/(kg·m2)A/(kg·m2)L/m${\delta _{\text{D}}}$/(°)
    45.500.9020.1631.7920.4955
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-12-01
  • 录用日期:  2022-02-20
  • 网络出版日期:  2022-02-21

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