Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : November 16, 2018
Thermal Protection Systems (TPS) is used to protect the spacecraft from heat generated during re-entry. The ablator is a typical example of TPS, which is generally composed of short carbon fiber and a resin. Thermal protection is realized by thermal decomposition of the resin and gas, carbonized layer In the present stydy,we developed new light weight ablator using three dimensionally networked porous carbon (TNPC) material as preform. Acrylic resin were selected as imprgnated resin into TNPC preform. In the present study, we evaluted peformance evaluation of porous carbon ablator with acrylic resin with the density of 0.48-0.8g/cm3 by using arc wind tunnel test. Thermal response was also also simulated by finitie element analysis. Experimental results showed that middle density ablator had good thermal properties and recession resistance in low heat flux compared with low density ablator. Analytical result didnot correospond to experimental result because sublimation of carbon, and endothermic reaction strongly contributed to temperature profile.
