Determination of high temperature thermoradiative properties of composite materials for the thermal protection of spacecraft

1995 ◽  
Vol 27/28 (3) ◽  
pp. 253-259 ◽  
Author(s):  
Joseph Giral ◽  
Daniel Hernandez ◽  
Bruno Rivoire ◽  
Jean-François Robert ◽  
Claude Royère ◽  
...  
Keyword(s):  
High Temperature ◽  
Composite Materials ◽  
Thermal Protection

Heat and mass transfer in thermal protection composite materials upon high temperature loading

2016 ◽  
Vol 54 (3) ◽  
pp. 390-396 ◽  
Author(s):  
V. F. Formalev ◽  
S. A. Kolesnik ◽  
E. L. Kuznetsova ◽  
L. N. Rabinskii
Keyword(s):  
Mass Transfer ◽  
High Temperature ◽  
Composite Materials ◽  
Heat And Mass Transfer ◽  
Thermal Protection

Analysis and Testing of Dynamic Micromechanical Behavior of Composite Materials at Elevated Temperatures

1996 ◽  
Vol 118 (4) ◽  
pp. 554-560 ◽  
Author(s):  
R. H. Pant ◽  
R. F. Gibson
Keyword(s):  
High Temperature ◽  
Composite Materials ◽  
Elevated Temperatures ◽  
Flexural Modulus ◽  
Flexural Vibration ◽  
Unidirectional Composite ◽  
Vibration Test ◽  
Impulse Frequency ◽  
Composite Moduli

This paper describes the use of a recently developed high temperature impulse-frequency response apparatus to directly measure dynamic modulus and internal damping of high temperature composite materials, matrix materials, and reinforcing fibers as a function of temperature. An extensional vibration test was used for determination of the complex Young’s modulus of fiber specimens as a function of temperature. A flexural vibration test was used for determination of the complex flexural modulus of matrix and unidirectional composite specimens (0 and 90 deg fiber orientations) as a function of temperature. These results were obtained from tests done on two different fiber reinforced composite materials: boron/epoxy (B/E) and Silicon Carbide/Ti-6Al-4V (SiC/Ti). The results from these tests were then used to assess the validity of micromechanics predictions of composite properties at elevated temperatures. Micromechanics predictions of composite moduli and damping at elevated temperatures show good agreement with measured values for the 0 deg case (longitudinal) but only fair agreement for the 90 deg case (transverse). In both cases, the predictions indicate the correct trends in the properties.

scholarly journals Hybrid Carbon-Carbon Ablative Composites for Thermal Protection in Aerospace

2014 ◽  
Vol 2014 ◽  
pp. 1-15 ◽  
Author(s):  
P. Sanoj ◽  
Balasubramanian Kandasubramanian
Keyword(s):  
High Temperature ◽  
Composite Materials ◽  
Thermal Protection ◽  
Coefficient Of Thermal Expansion ◽  
Cost Effective ◽  
Thermomechanical Properties ◽  
Substrate Material ◽  
Space Vehicles ◽  
External Temperature ◽  
Heat Shielding

Composite materials have been steadily substituting metals and alloys due to their better thermomechanical properties. The successful application of composite materials for high temperature zones in aerospace applications has resulted in extensive exploration of cost effective ablative materials. High temperature heat shielding to body, be it external or internal, has become essential in the space vehicles. The heat shielding primarily protects the substrate material from external kinetic heating and the internal insulation protects the subsystems and helps to keep coefficient of thermal expansion low. The external temperature due to kinetic heating may increase to about maximum of 500°C for hypersonic reentry space vehicles while the combustion chamber temperatures in case of rocket and missile engines range between 2000°C and 3000°C. Composite materials of which carbon-carbon composites or the carbon allotropes are the most preferred material for heat shielding applications due to their exceptional chemical and thermal resistance.

Trends in the development of flexible thermal protection systems for modern aircraft

2020 ◽  
pp. 10-21
Author(s):  
V. G. Babashov ◽  
◽  
N. M. Varrik ◽  
Keyword(s):  
High Temperature ◽  
Thermal Protection ◽  
Heat Removal ◽  
Operating Conditions ◽  
Passive Protection ◽  
Thermal Protection Systems ◽  
Heat Protection ◽  
Protection Systems ◽  
Protected Surface ◽  
Flexible Panels

The emergence of new types of space and aviation technology necessitates the development of new types of thermal protection systems capable of operating at high temperature and long operating times. There are several types of thermal protection systems for different operating conditions: active thermal protection systems using forced supply of coolant to the protected surface, passive thermal protection systems using materials with low thermal conductivity without additional heat removal, high-temperature systems, which are simultaneously elements of the bearing structure and provide thermal protection, ablation materials. Heat protection systems in the form of rigid tiles and flexible panels, felt and mats are most common kind of heat protecting systems. This article examines the trends of development of flexible reusable heat protection systems intended for passive protection of aircraft structural structures from overheating.

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