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The Simulation of Aerodynamic Heating and Ablation for a Hypervelocity Projectile(PDF)

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2003年05期
Page:
595-602
Research Field:
Publishing date:

Info

Title:
The Simulation of Aerodynamic Heating and Ablation for a Hypervelocity Projectile
Author(s):
WangZhongyuan ShiJinguang
School of Power Engineering,NUST,Nanjing 210094
Keywords:
hypervelocity project iles and rocket s aerodynamic heat ing ablation
PACS:
TJ012.3
DOI:
-
Abstract:
The phenomenon of aerodynamic heat ing and ablation for hypervelocity projectues seriously af fects the characteristics of the exterior ballist ics. In this paper, the aim is to establish perfectly aerody namic heat ing and ablat ion model for these project iles. Wing-body aerodynamic interference is studied by small perturbat ion theory. At tack angle ( non-symmet ry) is considered by use of the axisymmetric analog method. Ablation rules are conf irmed w ith thermochemist ry reaction technique in hig h temperature. The simulat ion of aerodynamic heat ing and ablat ion is carried out w ith instances. Some helpful results are concluded according to simulat ion. All of these are useful for further research.

References:

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2 Landau H G. Heat conduction in a melting solid[ J] . Quarterly of Applied Mathematics, 1950, 8( 81) : 81~ 94.
3 Canton-Desmeuzes C, Pirotails D, de Winne J. Hy pervelocity projectiles nosetip survivability to ablative and erosive environments[ A] . Niekerk C V. 17th I nternatio nal
Symposium on Ballistics[ C] .Midrand, South Africa: The South African Ballistics Organisation, 1998. 249~ 257.
4 刘建忠, 王中原. 高超音速弹丸表面气动加热及烧蚀现象研究[ J] . 南京: 南京理工大学学报,1999, 23( 1) : 53~ 56.

Memo

Memo:
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Last Update: 2013-03-17