원문정보
Rupture Characteristics of High Strength 3-Way Pyrovalve for Propulsion Engine of Space Launch Vehicle Liquid Rocket
초록
영어
In this paper, based on the existing research, we define the parameters for the number of ignition devices to be applied to the pyrovalve, the operation and airtightness according to the temperature, the material of the nipple and the thickness of the fractured part, and ANSYS Ver. 19.2 was used to analyze the FEA model, and a comparative analysis was conducted through structure analysis according to the piston shape of the pyrovalve. In addition, an experimental study was conducted by manufacturing a prototype according to the design variables. As a result, high-strength pyrovalves can stably supply working fluids such as fuel and oxidizer for space launch vehicle propulsion engines, as well as precisely control flow path switching was confirmed.
목차
1. 서론
2. 전산수치해석 방법
2.1 고강도 3-way 밸브
2.2 전산수치해석 모델링
2.3 경계조건
3. 전산수치해석 결과
4. 시험장치 구성 및 방법
4.1 파단하중시험
4.2 파이로밸브 작동시험
4.3 기밀ㆍ강도시험
5. 시험 결과 및 고찰
5.1 파단하중시험 결과
5.2 작동시험 결과
5.3 기밀ㆍ강도시험 결과
6. 결론
후기
References