Thermal Design and Dynamic Analysis of Metallic Thermal Protection System

2014 ◽  
Vol 912-914 ◽  
pp. 427-432 ◽  
Author(s):  
Hong Yong Chen ◽  
Hai Bo Chen
Keyword(s):  
Thermal Protection ◽  
Thermal Contact ◽  
Space Vehicle ◽  
Fem Analysis ◽  
Optimization Method ◽  
Thermal Protection System ◽  
Thermal Design ◽  
Protection System ◽  
Thermal Mode ◽  
Conduction Model

Metallic thermal protection system (MTPS) is a key component in space vehicle design. By introducing thermal contact resistance (TCR) on the interface between different layers of MTPS, an one dimensional (1D) thermal conduction model for MTPS with multiple functions is established for thermal design. An optimization method is proposed to determine the thermal parameter by comparing the results of 1D finite differential simulation with the test ones. The thermal mode is analyzed by three dimensional FEM analysis and the results show that the mechanical characteristics of MTPS appear to be asymmetric which provides a new consideration to insulate the fluctuating load.

Role of Thermal Contact Conductance on Sandwich-Type Metallic Thermal Protection System Profile

AIAA Journal ◽  
2012 ◽  
Vol 50 (10) ◽  
pp. 2194-2201 ◽  
Author(s):  
R. Ramesh Kumar ◽  
R. Palininathan ◽  
E. Kishor ◽  
G. Sunil Kumar ◽  
B. Deependran
Keyword(s):  
Thermal Protection ◽  
Thermal Contact ◽  
Thermal Protection System ◽  
Protection System ◽  
Thermal Contact Conductance ◽  
Contact Conductance ◽  
Sandwich Type

The Understanding of Thermomechanical Analysis of a Thermal Protection System

2013 ◽  
Vol 753-755 ◽  
pp. 1467-1476
Author(s):  
Xiao Bo Peng
Keyword(s):  
Thermal Stresses ◽  
Thermal Protection ◽  
Space Shuttle ◽  
Space Vehicle ◽  
Temperature Limit ◽  
Thermal Protection System ◽  
Protection System ◽  
Aerodynamic Heating ◽  
Transient Temperature ◽  
Vehicle Structure

Nowadays, reusable launch vehicle (RLV) has become a research focus of the transportation system between ground and space and the space weapon system. RLV plays an important role in controlling the cost of space transportation and performing the orbital mission. Since RLV would suffer from the aerodynamic heating inevitably during reentry, the thermal protection system (TPS) is designed to prevent too much heat transmitting to the vehicle structure and maintain the vehicle structure below a specified temperature limit. Several studies were performed to develop an understanding of not only the thermal and structural analysis of ceramic tile thermal protection system on the space shuttle but also the controlling factors of TPS. The TPS is subjected to the reentry heating and pressure profile of the Access to Space vehicle, and the transient temperature distribution and the resultant thermal stresses in the system are computed. Comparisons between various studies based on different assumptions were examined. By comparing these results with more realistic ones, the differences are evaluated. Results suggest that the TPS analysis must be based on reasonable and realistic parameters. Thus, engineers have to keep in mind that all parameters should be chosen very carefully to achieve results that close to practical ones.

Study of Ablative Thermal Protection System with Density Gradient

2021 ◽  
Vol 19 (1) ◽  
pp. 116-122
Author(s):  
Toshiyuki SUZUKI ◽  
Yuki KUBOTA ◽  
Yuichi ISHIDA ◽  
Takuya AOKI ◽  
Kazuhisa FUJITA ◽  
...  
Keyword(s):  
Density Gradient ◽  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System
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