액체 로켓 엔진 극저온 LOX 산화제의 충진 및 연소시험시 거동 특성

다국어 초록 (Multilingual Abstract)

The cryogenic characteristics of propellant is important parameter in the design of liquid rocket engine test facility. Pressure-fed rocket engine test facility with cryogenic propellant should be designed with considering cryogenic characteristics, vaporization should be avoided up to injection point. In this paper, characteristics of cryogenic liquid oxygen was examined during cold flow and combustion test of KSR-Ⅲ main engine at each stage. The effect of venting was examined at the stage of cooling and at the pressurization stage the interaction between nitrogen gas and liquid oxygen was also examined. The characteristic of liquid oxygen in the engine manifold was analyzed. To meet the pressure requirements during propellant outflow, the pressure in the upstream of engine was diminished rapidly, the effect of liquid oxygen was examined at rapid expansion. The results showed that venting was the primary role at the cooling process and the interaction of nitrogen gas and liquid oxygen in the run tank is limited at the surface area and the tests showed that the fluctuation of liquid oxygen flow was diminished at the combustion test and the expansion of liquid oxygen was contributed to the temperature rise of liquid oxygen.

목차 (Table of Contents)

• Abstract
• 1. 서론
• 2. 이론적 고찰
• 3. 시험설비 구성
• 4. 시험결과 및 토의
• 4. 결론
• 후기
• 참고문헌