Thermo-structural design of ZrB2-SiC-based thermal protection system for hypersonic space vehicles

2017 ◽  
Vol 100 (4) ◽  
pp. 1618-1633 ◽  
Author(s):  
Anupam Purwar ◽  
Bikramjit Basu
Keyword(s):  
Structural Design ◽  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Space Vehicles

Multilayer SiC for thermal protection system of space vehicles with decreased thermal conductivity through the thickness

2010 ◽  
Vol 30 (8) ◽  
pp. 1833-1840 ◽  
Author(s):  
S. Biamino ◽  
A. Antonini ◽  
C. Eisenmenger-Sittner ◽  
L. Fuso ◽  
M. Pavese ◽  
...  
Keyword(s):  
Thermal Conductivity ◽  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Space Vehicles

Pulsed Thermography and Ultrasonic Non-Destructive Evaluation of Corrugated Metallic Thermal Protection System (MTPS) Panel

2012 ◽  
Vol 710 ◽  
pp. 594-599
Author(s):  
S. Hari Krishna ◽  
Ajay Kumar ◽  
P. Karthikeyan ◽  
M.P. Abilash ◽  
N. Narayanankutty ◽  
...  
Keyword(s):  
Ultrasonic Testing ◽  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Aerodynamic Heating ◽  
Space Vehicles ◽  
Pulsed Thermography ◽  
Brazed Joints ◽  
Brazed Joint ◽  
Pulse Echo

Space vehicles that re-enter earth’s atmosphere require thermal protection system (TPS) to safeguard them from intense aerodynamic heating. Depending on the type of re-entry (lifting/ballistic), trajectory, duration of flight in atmospheric regime etc., the heat flux may vary from 40kW/m2to 180kW/m2. In our studies on metallic TPS (MTPS), corrugated core is joined to either side of the skins by brazing. The brazed joint is evaluated using both pulsed thermography (PT) and ultrasonic testing. PT images show clear visualization of joint and defects. Also it is faster and easier. Ultrasonic testing is done using pitch-catch and pulse-echo techniques, which shows many limitations. In literature, it is reported that for brazed joints using ultrasonic testing, defect location can be identified by faster decay pattern of multiple echoes (compared to that of good location). In case of PM 2000 panel, reversal of the patterns is observed. This new phenomenon is verified with the support of PT. It is also found that for inconel panel, the decay patterns are as reported in literature.

Thermal Impact Resistance of Integrated Thermal Protection System of Space Vehicles

2015 ◽  
Vol 1091 ◽  
pp. 103-108
Author(s):  
Xu Ji Fan
Keyword(s):  
Thermal Protection ◽  
Impact Resistance ◽  
Thermal Protection System ◽  
Protection System ◽  
Space Vehicles ◽  
Aerodynamic Pressure ◽  
Temperature Capability ◽  
Materials Used ◽  
Integrated Thermal Protection System ◽  
Single Material

Space vehicles which enter earth’s atmosphere require a thermal protection system (TPS) to protect them against aerodynamic pressure and heating impact. The use of material with high temperature capability in combination with low thermal conductivity, to limit transfer of heat into interior of the structure, is required of the TPS. Because these requirements cannot be accomplished by a single material layer, two material layers are proposed, and their functions are integrated through the TPS design. Future reentry vehicle’s capabilities will in great extent depend upon the capabilities of the materials used for these layers [1]. This paper is devoted to the protection layer of the TPS, to predict its strength and life under the aerodynamic pressure and heat impact loads.

Multilayer SiC for thermal protection system of space vehicles: Manufacturing and testing under simulated re-entry conditions

2008 ◽  
Vol 28 (14) ◽  
pp. 2791-2800 ◽  
Author(s):  
S. Biamino ◽  
V. Liedtke ◽  
C. Badini ◽  
G. Euchberger ◽  
I. Huertas Olivares ◽  
...  
Keyword(s):  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Space Vehicles

Preliminary tests for an intelligent thermal protection system for space vehicles

2001 ◽  
Author(s):  
Antonio Paolozzi ◽  
Ferdinando Felli ◽  
Teodore Valente ◽  
Michele A. Caponero ◽  
Mario Tului
Keyword(s):  
Thermal Protection ◽  
Thermal Protection System ◽  
Protection System ◽  
Space Vehicles

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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