한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제42권7호
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  • Pages.552-560
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  • 2014
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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펄스 데토네이션 엔진 이론 성능 예측 프로그램

Theoretical Performance Prediction Program of Pulse Detonation Engines

  • 투고 : 2014.04.01
  • 심사 : 2014.06.11
  • 발행 : 2014.07.01
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초록

Pulse Detonation Engine (PDE)는 압축 효과에 따른 효율 증가와 정지 상태로부터 높은 초음속구간까지 작동가능하다는 등의 장점으로 인해 차세대 고속추진기관으로 많은 연구가 진행되고 있다. 본 연구에서는 Chapman-Jouguet 데토네이션 이론과 일정 단면적의 관내 압축성 기연 가스 팽창과정을 연계한 Endo 이론을 바탕으로 실제 추진제에 대한 효율적인 PDE 이론 성능 예측 프로그램을 개발하였다. 성능 예측 프로그램은 탄도진자 측정을 통하여 얻은 실험 결과와 비교를 통하여 검증하였다. 이 프로그램을 이용하여 당량비, 초기압력 및 초기 온도 및 압력에 대한 성능 특성을 살펴보았고 다양한 탄화수소 연료, 산화제 조성에 대한 성능을 해석하여 PDE 이론 성능 데이터베이스를 구축하였다.

Pulse Detonation Engine(PDE) has been investigated as a next generation propulsion system with the advantages of the higher thermal efficiency by the compression effect and the wide operation ranges from zero speed at ground. In the present study, an efficient theoretical PDE performance prediction program was developed for realistic propellants based on the Endo's theory combining the Chapman-Jouguet detonation theory and expansion process of burnt gas in a constant area tube. The program was validated through the comparison with the experimental data obtained by a ballistic pendulum measurement. PDE performance analyses were carried out for various hydrocarbon fuels and oxidizer compositions by changing the mixture equivalence ratio and initial conditions. Theoretical PDE performance database could be established as a result of the analyses.

키워드

참고문헌

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피인용 문헌

  1. 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
  2. The Experimental Study about the Effect of Operating Conditions on Multi-tube Pulse Detonation Engine Performance vol.19, pp.1, 2018, https://doi.org/10.1007/s42405-018-0026-2