Thermophysical properties of high thermal conductivity graphite sheet for spacecraft thermal design

LiGaS2 crystals are grown, and the high thermal conductivity is established. Analysis of temperature dependences of various properties reveals side phases, and isotropic points in birefringence, photo-, thermo-, and pyroluminescence.

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The Thermal Expansion Behaviors of Cu-SiCp Composites

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.795.237 ◽

2013 ◽

Vol 795 ◽

pp. 237-240

Author(s):

K. Azmi ◽

M.N. Derman ◽

Mohd Mustafa Al Bakri Abdullah

Keyword(s):

Thermal Conductivity ◽

Silicon Carbide ◽

Thermal Expansion ◽

Thermal Management ◽

Thermophysical Properties ◽

Copper Matrix ◽

Experimental Results ◽

High Thermal Conductivity ◽

Coating Process ◽

Electroless Coating

The demand for advanced thermal management materials such as silicon carbide reinforced copper matrix (Cu-SiCp) composites is increasing due to their high thermal conductivity and low CTE properties. However, the weak bonding between the copper matrix and the SiCp reinforcement degrades the thermophysical properties of the composites. In order to improve the bonding between the two constituents, the SiCp were copper coated (Cu-Coated) via electroless coating process. Based on the experimental results, the CTE values of the Cu-Coated Cu-SiCp composites were found significantly lower than those of the non-Coated Cu-SiCp composites. The CTEs of the Cu-Coated Cu-SiCp composites were in agreement with Kernels model which accounts for both the shear and isostatic stresses developed in the component phases.

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Advanced Conductive Composite Materials for Spacecraft Application

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.123-125.7 ◽

2010 ◽

Vol 123-125 ◽

pp. 7-10

Author(s):

Ho Sung Lee

Keyword(s):

Thermal Conductivity ◽

Composite Material ◽

Composite Materials ◽

Carbon Fiber ◽

High Performance ◽

Thermal Stresses ◽

Thermal Design ◽

High Thermal Conductivity ◽

Carbon Fiber Composites ◽

Advanced Composite

In this study, thermal responses of advanced fiber/epoxy matrix composite materials are considered for spacecraft thermal design. These thermal responses are important, because the localized thermal behavior from applied heat loads can induce thermal stresses, which can lead to functional failure of the spacecraft system. Since most of polymer matrices exhibit relatively poor thermal conductivity, the composite materials have been widely considered only for structural application and little for thermal application. However, recently pitch-based high performance carbon fiber becomes available and this fiber shows high thermal conductivity. Because of this combination of low CTE and high thermal conductivity, continuous carbon fiber composites make them suitable for thermal management of spacecraft. The advanced composite material is composed of a continuous high modulus pitch based fiber (YS90A) and DGEBA epoxy resin(RS3232). It was demonstrated that advanced composite material satisfied thermal requirement for a lightweight thermal radiator for heat rejection of communication satellite.

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