한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제19권6호
  • /
  • Pages.10-18
  • /
  • 2015
  • /
  • 1226-6027(pISSN)
  • /
  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
권호 표지
DOI QR코드

DOI QR Code

로켓기반 공기흡입추진 엔진이 적용된 재사용 발사체의 요구 성능 및 중량 분석

Performance Requirement Analysis and Weight Estimation of Reusable Launch Vehicle using Rocket based Air-breathing Engine

  • Lee, Kyung-Jae (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Yang, Inyoung (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Lee, Yang-Ji (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Kim, Chun-Taek (Engine System Research Team, Korea Aerospace Research Institute) ;
  • Yang, Soo-Seok (Aero propulsion Division, Korea Aerospace Research Institute)
  • 투고 : 2015.09.24
  • 심사 : 2015.11.11
  • 발행 : 2015.12.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

로켓 기반 공기흡입추진(RBCC : Rocket Based Combined Cycle) 엔진이 적용된 재사용 발사체의 요구 중량 및 성능을 분석하고 예측하였다. RBCC 엔진을 위해 개발한 엔진 모델과 비행체 궤적 모델을 통합하여 RBCC 기반 재사용 발사체의 궤적 및 성능계산 모델을 개발하였으며, 기존 논문의 결과와 비교함으로써 검증하였다. 개발된 모델과 기존 논문을 바탕으로 총 이륙중량 15톤의 재사용 발사체에 대한 무게분석과 엔진의 요구 조건을 도출하였으며, 엔진의 모드 전환 마하수 변화 등에 따른 비행체의 추진제 요구량 변화를 분석하였다.

Performance requirement analysis and weight estimation of a reusable launch vehicle with a rocket-based air-breathing engine(RBCC : Rocket Based Combined Cycle) were performed. Performance model for an RBCC engine was developed and integrated with flight trajectory model. The integrated engine-trajectory model was validated by comparing the results with those from previous research reference. Based on the new engine-trajectory model and previous research results, engine performance requirements were derived for an reusable launching vehicle with gross take-off weight of 15 tones. Dependence of the propellant amount requirement on the mode transition Mach number of the engine was also analyzed.

키워드

참고문헌

  1. Andreadis, D., Scramjet Engines Enabling the Seamless Integration of Air & Space Operation, Pratt & Whitney Space Propulsion, Hypersonics, West Palm Beach, FL, USA, 2004.
  2. Yugov, O.K. et al., "Optimal Control Programs for Airbreathing Propulsion System for Single-Stage-To-Orbit," 40th IAF Congress, Malaga, Spain, IAF-89-308, Oct. 1989.
  3. Kanda, T., Tomioka, S., Ueda, S., Tani, K. and Wakamatsu, Y., "Design of Sub-scale Rocket-Ramjet Combined Cycle Engine Model," 56th International Astronautical Congress, Fukuoka, Japan, IAC-05-C4.5.03, Oct. 2005.
  4. Kang, S.H. and Lee, S.Y., "Weight Reduction of the Reusable Launch Vehicles Using RBCC Engines", Journal of the Korean Society of Propulsion Engineers, Vol. 17, No. 3, pp. 56-66. 2013. https://doi.org/10.6108/KSPE.2013.17.3.056
  5. Lee, Y.J., Kang, S.H. and Yang, S.S., "Conceptual Design of Rocket Based Combined Cycle Engine," 33th KSPE Fall Conference, Kyungju, Korea, pp. 581-585, Nov. 2009.
  6. Olds, J.R. and Bradford, J.E., "SCCREAM: A Conceptual Rocket-Based Combined-Cycle Engine Performance Analysis Tool," Journal of Propulsion and Power, Vol. 17, No. 2, pp. 333-339, 2001. https://doi.org/10.2514/2.5746
  7. Takahashi, S., Mizobata, K. and Sawada, K., "Conceptual Study of a Two-Stage Air-Breading Reusable Launch Vehicle," Journal of Spacecraft and Rockets, Vol. 34, No. 5, pp. 628-635, 1997. https://doi.org/10.2514/2.3280
  8. Olds, J.R., "Results of a Rocket-Based Combined-Cycle SSTO Design Using Parametric MDO Methods," SAE-941165, 1994.
  9. Mizobata, K., Kimura, H., Sugiyama, H., Sato, T. and Kobayashi, H., "Conceptual Design of Flight Demonstrator Vehicles for the ATREX Engine," 12th AIAA International Space Planes and Hypersonic Systems and Technologies, Norfolk, VA, USA, AIAA 2003-7028, Dec. 2003.
  10. Olds, J.R., "Multidisciplinary Design Techniques Applied to Conceptual Aerospace Vehicle Design," NASA-CR-194409, 1993.
  11. Saha, S. and Chakraborty, D., "Hypersonic Intake Starting Characteristics - A CFD Validation Study," Defence Science Journal, Vol. 62, No. 3, pp. 147-152, 2012. https://doi.org/10.14429/dsj.62.1340

피인용 문헌

  1. Ramjet Mode Combustion Test for a Dual-Mode Ramjet Engine Model with a Large Backward-Facing Step vol.20, pp.6, 2016, https://doi.org/10.6108/KSPE.2016.20.6.083
  2. Effect of thermal choking on ejection process in a rocket-based combined cycle engine vol.116, 2017, https://doi.org/10.1016/j.applthermaleng.2017.01.059
  3. Technology Development Prospects and Direction of Reusable Launch Vehicles and Future Propulsion Systems vol.44, pp.8, 2016, https://doi.org/10.5139/JKSAS.2016.44.8.686