Using C/SiC Composite Materials for Thermal Protection System for Planetary Entry System, Behaviour in Relevant Environment

1995 ◽  
Author(s):  
Marc Lacoste ◽  
Frédéric Fenot ◽  
Alain Lacombe ◽  
Michel Cataldi

A Thermal protection system is used to protect the rocket from the heat generated by the hot gases. A thermal boot is used as the thermal protection system at the outside of the nozzle to protect the flex seal. The objective of the present work is to design the thermal protection system for flex seal using different composite materials for single time of flight and to study the ablation of the materials. The problem is modelled using commercial ANSYS software. 3-D Axi-symmetric transient thermal analysis is performed for the flex seal along with thermal protection system made of composite materials. The initial and boundary conditions are applied to meet the industrial requirement. From this analysis, thermal protection system made of different composite materials is studied and one is suggested based on ablation and weight reduction.


Author(s):  
Michael Wright ◽  
Ioana Cozmuta ◽  
Bernard Laub ◽  
Yih-Kanq Chen ◽  
William H. Wilcoxson

Author(s):  
Toshiyuki SUZUKI ◽  
Yuki KUBOTA ◽  
Yuichi ISHIDA ◽  
Takuya AOKI ◽  
Kazuhisa FUJITA ◽  
...  

2002 ◽  
Author(s):  
M. Blosser ◽  
R. Chen ◽  
I. Schmidt ◽  
J. Dorsey ◽  
C. Poteet ◽  
...  

2010 ◽  
Vol 30 (8) ◽  
pp. 1833-1840 ◽  
Author(s):  
S. Biamino ◽  
A. Antonini ◽  
C. Eisenmenger-Sittner ◽  
L. Fuso ◽  
M. Pavese ◽  
...  

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