Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지

Numerical Analysis on the Startup of a Rocket Engine

로켓 엔진의 시동에 관한 해석적 연구

  • 박순영 (한국항공우주연구원 엔진팀) ;
  • 설우석 (한국항공우주연구원 엔진팀)
  • Published : 2007.10.30
Download PDF
⟨ Previous Next ⟩

Abstract

The startup characteristic of liquid propellant rocket engine should be focused on the stable ignition of combustion chamber and gas generator. Also, to lessen the propellants consumption during this period which doesn't contribute to the flight thrust, the engine has to be transferred to the nominal mode quickly. Because of the risk of test, it is impossible to develop all the startup cyclogram or the specifications of engine by test, so the precedent numerical approach is quite necessary. In this study we developed a mathematical model for the startup phenomena in a liquid rocket engine driven by gas generator-turbopump system based on the commercial 1-D flow system analysis program, Flowmaster. Using this program we proposed a methodology to obtain the specifications of turbine starter and the opening time of shutoff valves for the stable startup of the engine. To verify this methodology we qualitatively compared the analysis results to the typical startup curve of the published engine, then found it is quite well matched.

액체로켓 엔진의 시동은 연소기와 가스발생기의 안정적인 점화는 물론 시동에 소요되는 시간을 단축하여 추력 발생과 상관없는 추진제 소모량을 줄이는 방향으로 전개되어야 한다. 특히 엔진시스템의 시동 순서나 규격을 모두 시험적으로 개발하는 데는 한계가 있으며, 안전상의 이유로 시험 조건이나 시동 cyclogram에 대한 해석적인 분석이 선행될 필요가 있다. 이에 본 연구에서는 가스발생기 사이클 액체로켓 엔진의 수학적 모델을 상용 1차원 유체시스템 해석 프로그램인 Flowmaster를 기반으로 개발하였으며, 이를 이용하여 안정된 엔진 시동을 위한 파이로시동기 규격이나 연소기 및 가스발생기 종단밸브의 열림시간 등을 구하는 방법론을 제시하였다. 아울러 해석 결과로 구한 시동특성을 해외 엔진의 시동 해석 결과와 정성적인 비교를 수행하여 비교적 잘 일치함을 파악하였다.

Keywords

References

  1. Kanumuri, A., Wakamatsu, Y., Shimura, K., Toki, K., and Torii, Y., "Start Transient Analysis of Turbopump-fed LOx/LH2 Rocket Engine (LE-5)," AIAA-89-2736
  2. Paulo, C. T., "Dynamic Models for Liquid Rocket Engines with Health Monitoring Application," MIT Master degree thesis, 1998
  3. Liu, K., and Zhang, Y., "A Study on Versatile Simulation of Liquid Propellant Rocket Engine Systems Transients," 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit pp. 1-12, AIAA-2000-3771
  4. E. K. Ruth, H. Ahn, R. L. Baker, and M. A. Brosmer, "Advanced Liquid Rocket Engine Transient Model," AIAA-90-2299
  5. Michael, B., "A Transient Model of the RL10A-3-3A Rocket Engine," AIAA-95-2968
  6. Frank E. M., Servo-Stabilization of Low-Frequency Oscillations in Liquid Propellant Rocket Motors, 1955
  7. McBride, B. J. and Gordon, S., "Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications,󰡓NASA Reference Publication 1311, 1996
  8. 한영민, 김승한, 문일윤, 김홍집, 김종규, 설우석, 이수용, 권순탁, 이창진, "충돌형 분사기 형태의 액체로켓 엔진용 가스발생기 연소성능시험," 한국추진공학회지, 제8권 제2호, 2004, pp.10-17
  9. Flowmaster Reference Help, ver. 7.0, 2007
  10. NASA SP 8097, "Liquid Rocket Valve Assemblies," 1973, pp.11
  11. NASA SP-8107, "Turbopump Systems for Liquid Rocket Engines," 1974, pp.86
  12. H. Karimi and E. E. Taheri, "Simulation of the Internal Ballistics of a Liquid Propellant Engine Start System in Comparison with Experimental Verification," 2006 European Conference on Computational Fluid Dynamics, 2006
  13. Rocketdyne, "F-1 Rocket Engine Data Manual," NASA-CR-143972, 1967
  14. Chrysler, "H-1 Engine and Hydraulic System," SA-7 Vehicle and Launch Complex Functional Description, 1964
  15. Mark F. and Michael I., "Low-Cost Propulsion Technology at the Marshell Space Flight Center - Fastrac Engine and the Propulsion Test Article," AIAA-98-3365