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Preliminary Design Plan for Determining Combustor Configuration of Regenerative-cooled Liquid Rocket Engine  

Son, Min (한국항공대학교 항공우주 및 기계공학과)
Seo, Min-Kyo (한국항공대학교 항공우주 및 기계공학과)
Koo, Ja-Ye (한국항공대학교 항공우주 및 기계공학부)
Cho, Won-Kook (한국항공우주연구원 발사체엔진팀)
Seol, Woo-Seok (한국항공우주연구원 발사체엔진팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.15, no.1, 2011 , pp. 83-89 More about this Journal
Abstract
A design plan was proposed for determining combustor configuration of regenerative- cooled liquid rocket engine in the process of preliminary design. Rocket performance and regenerative cooling results were calculated using the properties of combustion gas estimated in CEA. For required thrust, chamber pressure, atmosphere pressure and propellant mixture ratio the mass flow rate of propellants and combustor performance were predicted by one-dimensional and experimental correlations. Finally, determinable plan for the contour of combustor were presented through Rao nozzle design method.
Keywords
Design Program; Combustor; Liquid Rocket Engine; Preliminary Design; Regenerative Cooling;
Citations & Related Records
Times Cited By KSCI : 4  (Citation Analysis)
연도 인용수 순위
1 Sanford Gordon, Bonnie J. McBride, "Computer Program for Calculation Complex Chemical Equilibrium Compositions and Applications," NASA RP-1311, October 1994
2 G.V.R. Rao, "Approximation of Optimum Thrust Nozzle Contour," ARS Journal, vol. 30, No. 6, Jun. 1960, p.561
3 eter K. Huzel and David H. Huang, Modern Engineering for Design of Liquid-propellant Rocket Engines, AIAA
4 R. T. Cook, "Advanced Cooling Techniques for High-pressure Hydrocarbon-fueled Engines," NASA CR-159790, 1979
5 Moody, L.F., "Friction Factors for Pipe Flow," Transactions of ASME, 1944, pp.671-684
6 Chen, N.H., "An Explicit Equation for Friction Factor in Pipe," Industrial & Engineering Chemistry Fundamentals, Vol. 18, No. 3, 1979, pp.296-297   DOI
7 NIST Thermophysical Properties of Hydrocarbon Mixtures Database (SUPERTRAPP) Version 3.2 Users' Guide
8 B. Mc Hugh, "Numerical Analysis of Existing Liquid Rocket Engines as a Design Process Starter", AIAA 95-2970
9 David W. Way, "SCORES : Developing an Object-Oriented Rocket Propulsion Analysis Tool," AIAA 98-3227, 1998
10 J. Bradford, "SCORES-II Design Tool for Liquid Rocket Engine Analysis," AIAA 2002-3990
11 J. E. Bradford, A. Charania and B. St. Germain, "REDTOP-2: Rocket Engine Design Tool Featuring Engine Performance, Weight, Cost, and Reliability," AIAA 2004-3514
12 이진근, 김진한, "터보펌프식 액체로켓엔진의 시스템 해석," 한국항공우주학회지, 제32권, 제5호, 2004, pp.109-115
13 조원국, 박순영, 설우석, "가스발생기 사이클로켓엔진 성능해석 프로그램 개발," 한국추진공학회지, 제12권, 제5호, 2008, pp.18-25
14 양희성, 박병훈, 윤웅섭, "액체 로켓 엔진시스템 개념설계를 위한 모듈화 프로그램 Part I : 주요 구성품 설계," 한국항공우주학회지, 제35권, 제9호, 2007, pp.805-815
15 박병훈, 양희성, 김원호, 윤웅섭, "액체 로켓엔진시스템 개념설계를 위한 모듈화 프로그램 Part II : 통합 모듈화 프로그램," 한국항공우주학회지, 제35권, 제9호, 2007, pp.816-825
16 Ronald Humble, Gary N. Henry and Wiley J. Larson, Space Propulsion Analysis and Design, McGraw-Hill, 1995