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.

• 강대희(네오스펙) | Dae Hee Kang
• 이효원(네오스펙) | Hyo Won Lee
• 정윤재(공주대학교 친환경지속가능에너지연구소) | Yoonjae Chung
• 김원태(공주대학교) | Wontae Kim Corresponding author