[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2015 , Vol. 35 >Issue 5: 119 - 122

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2015.05.029

BALLISIIC AND AIRDYNAMICS

Simulation of Internally Carried Air-launched Launch Vehicle Separation from Aircraft by Dynamic Grid

  • ZHENG Wuji ,
  • ZHANG Dengcheng ,
  • ZHANG Yanhua ,
  • LI Jingtao ,
  • ZHENG Wusuo
Expand
  • 1 Aeronautics and Astronautics College, Air Force Engineering University, Xi'an 710038, China
    2 The Second Training Brigade, Harbin Flight Academy, Harbin 150000, China

Received date: 2014-09-20

  Online published: 2025-05-28

Fold

Abstract

In order to simulate separation of air-launched launch vehicle from aircraft exactly, and obtain the law of separation characteristic of air-launched launch vehicle from aircraft in aircraft wake, the initial state calculation model of air-launched launch vehicle from the aircraft was built by hybrid grid; compared with calculation model of traditional unstructured grid, the model has higher computation efficiency. Separation characteristic of air-launched launch vehicle from the aircraft in the aircraft wake was studied by dynamic grid technology, and through comparison, the result shows that the influence of aircraft wake is in a certain range, it is unfavorable to the separation of airlaunched launch vehicle from the aircraft. The conclusion can provide reference for further study effect on security and stability characteristic of air-launched launch vehicle separation from aircraft.

Key words： internally carried air-launched launch vehicle; dynamic grid; hybrid grid; asymmetric vortex

Cite this article

ZHENG Wuji , ZHANG Dengcheng , ZHANG Yanhua , LI Jingtao , ZHENG Wusuo . Simulation of Internally Carried Air-launched Launch Vehicle Separation from Aircraft by Dynamic Grid[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2015 , 35(5) : 119 -122 . DOI: 10.15892/j.cnki.djzdxb.2015.05.029

[an error occurred while processing this directive]

References

[1]
李易, 唐硕, 许志. 内装式空中发射运载火箭重力出舱运动分析[J]. 飞行力学, 2009. 27 3: 62-65.
[2]
韩占中, 王敬, 兰小平. FLUENT 流体工程计算仿真计算实力与应用[M]. 北京: 北京理工大学出版社, 2010.
[3]
江帆, 黄鹏. FLUENT 高级应用与实例分析[M]. 北京: 清华大学出版社, 2008.
[4]
张久星, 张登成, 朱和铨, 等. 基于 ADAMS 的内装式空射运载火箭分离过程动力学分析[J]. 弹箭与制导学报, 2011. 31 2: 153-156.
[5]
王利荣. 降落伞理论与应用[M]. 北京: 宇航出版社, 1997.
[6]
朱和铨, 张登成, 屈亮, 等. 基于数值仿真的火箭箭体气动特性分析[J]. 弹箭与制导学报, 2012. 32 1: 142-444.
[7]
Marti Sarigul-Klijn, Nesrin Sarigul-Klijn, Gary C Hudson, et al. Gravity air launching of earth-to-orbit space vehicles, ΑΙΑΑ 2006-7256 [R]. 2006.
[8]
纪兵兵, 陈金瓶. ANSYS ICEM CFD 网格划分技术实例详解[M]. 北京: 中国水利水电出版社, 2012.
Options
Outlines

/

〈 〉

[an error occurred while processing this directive]