마이크로중력 비행 실험을 위한 연소실험장비의 구조해석

Abstract

This study had developed a combustion experiment system for a cool flame research in microgravity environment. For the development of the system, various combustion experiment devices used on the ISS were reviewed, and the shape, size, thickness, and material of the combustion chamber were designed by the standard requirements based on the Korea Standard (KS) and Japan Industrial Standard (JIS). The system was loaded on a reduced-gravity aircraft (so-called, parabolic flight campaign) at Zero-G Corporation in the United States for the cool flame experiment. For the experiment in the aircraft which simulated microgravity environment, structural analysis of a combustion chamber under the condition of pressurized and depressurized cases using a finite elements method was carried out. Furthermore, the factor of safety for the combustion system in the aircraft where hyper-gravity (9G) occurred was calculated. It was confirmed that the system was structurally safe for parabolic flight experiment under microgravity.