-
구독
구독함
이미 WordPress.com 계정을 가지고 계신가요? 바로 로그인하세요.
This research aimed to replace the combustion chamber material of a solid propellant rocket engine, which was traditionally made from aluminum (Al), with carbon fiber reinforced plastic (CFRP) to reduce theengine’s weight. Through structural analysis, potential failure causes in CFRP combustion chambers were identified and addressed, leading to a 10% weight reduction compared to the
Providing thrust testing equipment and supporting thrust testing for new participating schools in the National University Rocket Competition.
A hybrid rocket using HAN (Hydroxylammonium Nitrate)-based oxidizer was analyzed for its combustion characteristics. By synthesizing and concentrating the HAN solution to achieve a uniform concentration, a lab-scale combustion test setup and a 10 N class thrust engine were designed and built. Additionally, the oxidizer delivery system’s integrity and functionality were verified through hydraulic tests.
This research analyzed the phase transition behavior of Hydroxylammonium Nitrate (HAN), which is used as an oxidizer for monopropellants. After a prolonged vacuum concentration process, a 99.7 wt% HAN solution was obtained, and the phase transition behavior of HAN was observed under different storage conditions. It was found that solid HAN crystals precipitated when stored
HANul 