宇航学报 ›› 2019, Vol. 40 ›› Issue (7): 768-775.doi: 10.3873/j.issn.1000-1328.2019.07.005

• 飞行器设计与力学 • 上一篇    下一篇

高超声速导弹多场耦合仿真

徐世南,吴催生   

  1. 中国空空导弹研究院,洛阳 471000
  • 收稿日期:2018-08-07 修回日期:2018-11-26 出版日期:2019-07-15 发布日期:2019-07-25
  • 基金资助:

    航空科学基金(20155212009)

Simulation of Multi Field Coupling on Hypersonic Missiles

XU Shi nan, WU Cui sheng   

  1. China Airborne Missile Academy, Luoyang 471000, China
  • Received:2018-08-07 Revised:2018-11-26 Online:2019-07-15 Published:2019-07-25

摘要:

为准确预测高超声速导弹气动力与气动热环境,采用分区求解方法,实现气动力/热/结构多场耦合计算,并通过与试验值对比确立了耦合仿真方法的有效性。建立大长细比高超声速导弹仿真计算模型,对导弹弹体结构变形、温度场和压力场进行了数值模拟。仿真结果表明:弹体结构随着攻角增加发生轴向拉伸和横向弯曲;拉伸变形主要由气动热引起,弯曲变形主要由气动力引起;导弹头部气动热与气动力载荷大;耦合效应随着导弹攻角增加更加明显,造成导弹气动热力学环境更加严酷。

关键词: 导弹, 高超声速, 耦合, 大长细比, 数值模拟

Abstract:

An aerodynamic/thermal/structural multi-field coupling analysis is implemented using the partition algorithm in order to predict the aerodynamic and aerothermal environment accurately, and this coupling method is validated by comparing with the experiments. A slender hypersonic missile model is established and its structural deformation, temperature and pressure are numerically simulated. The results show that the structure is stretched longitudinally and bent laterally with the increment in attack angle; the stretching deformation is mainly caused by the thermal factor and the bending deformation is primarily caused by the aerodynamic factor; the aerodynamic and aerothermal environments are more harsh in the missile head; the coupling factors become obvious at large attack angle and aggravate the aerodynamic heating and aerodynamic environment.

Key words: Missile, Hypersonic, Coupling, Slender, Numerical simulation

中图分类号: