Experimental equipment for the evaluation of the strength characteristics of carbon-carbon composite mateials within the temperature range 20–2200°C

Negovskii, A. N.; Drozdov, A. V.; Kutnyak, V. V.; Nozhnitskii, Yu. A.; Menshikov, A. N.; Qiao, Shuqing

doi:10.1007/bf02511015

Cited by 4 publications

(2 citation statements)

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“…Fiber reinforced composite structures create explosion at high temperature (>2000 ∘ C) due to their organic content in the elemental composition. The fire reaction behaviour of structural composite materials and their characterization account for information such as their time-to-ignition, heat release rate, limiting oxygen index, flame spread, and smoke density [78]. The thermal, chemical, and mechanical behaviour of the composite panels during the fire exposure are effectively analyzed through structural response of composite and degradation kinetics.…”

Section: Thermal Analysis Of the Composite Materialsmentioning

confidence: 99%

“…Pyrolysis mechanism of the carbon-carbon composite is as same as other ablative materials in terms of thermal decomposition, char morphology, and delamination. In case of phenolic resin, the matrix decomposition takes place at a particular temperature followed by the char layer ablation at a little higher temperature [78]. Thermal response of carbon-carbon composite at various zones (virgin material zone, pyrolysis zone, and porous char layer zone) is different and the thermal analysis needs to consider for this variation in thermal response.…”

Section: Mathematical Model Of Phenolic Impregnated Carbonmentioning

confidence: 99%

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Hybrid Carbon-Carbon Ablative Composites for Thermal Protection in Aerospace

Sanoj

Kandasubramanian

2014

Journal of Composites

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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.

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Section: Thermal Analysis Of the Composite Materialsmentioning

confidence: 99%

Section: Mathematical Model Of Phenolic Impregnated Carbonmentioning

confidence: 99%