발사대기 중인 액체추진 로켓의 극저온 산화제 탱크 내 비정상 열해석

다국어 초록 (Multilingual Abstract)

The prelaunch thermal transients in the cryogenic oxidizer tank of liquid propulsion rocket subjected to uniform heat flux from outside are numerically analyzed through thermodynamic equations and heat and mass transfer relations. The prelaunch stage is assumed to be composed of five idealized sub-stages including pressurization process by helium gas injection. The Peng-Robinson equation of state is utilized in the lumped analysis of ullage gas. The liquid region is divided into a number of horizontal layers of uniform properties to account for the thermal stratification. The computational result for the typical case shows that the temperature rise of liquid oxidizer is less than 1K and the adsorbed helium into the liquid is approximately 10g.

참고문헌 (Reference)

1 조남경, "추진제 탱크내의 액체산소 온도상승에 대한 해석적 고찰" 한국추진공학회 9 (9): 25-37, 2005

2 조남경, "액체 로켓 추진 시스템의 저온관련 기술 발전 동향" 7 (7): 39-43, 2005

3 이희준, "소형위성 발사체용 추진제 가압 열교환기 설계 해석" 한국전산유체공학회 9 (9): 49-56, 2004

4 정용갑, "극저온 헬륨가스 가압시스템에 대한 온도특성 연구(I)" 한국추진공학회 9 (9): 66-73, 2005

5 Ring, E., "Rocket Propellant and Pressu- rization Systems" Prentice Hall 1964

6 Benitez, J., "Principles and Modern Appli- cations of Mass Transfer Operations" John Wiley & Sons 2002

7 Hwang, S. H., "Overview of scientific payloads onboard the KSR-Ⅲ rocket" 60 : 880-888, 2007

8 Cengel, Y. A., "Heat Transfer: A Practical Approach" McGraw-Hill 2003

9 Koretsky, M. D., "Engineering and Chemical Thermodynamics" John Wiley & Sons 2004

10 Burmeister, L. C., "Convective Heat Transfer" John Wiley & Sons 1993