한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제18권2호
  • /
  • Pages.16-26
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  • 2014
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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고체로켓 연소관 내 압력섭동에 대한 입자상 물질에 의한 음향 감쇠 및 연소응답 특성 측정

Measurement of Pressure-coupled Combustion Instability Characteristics : Acoustic Attenuation by Particulate Matter(Al) and Combustion Response of Solid Propellant

  • Lim, Jihwan (School of Mechanical Engineering, Yonsei University) ;
  • Lee, Sanghyup (School of Mechanical Engineering, Yonsei University) ;
  • Yoon, Woongsup (School of Mechanical Engineering, Yonsei University)
  • 투고 : 2013.12.02
  • 심사 : 2014.03.08
  • 발행 : 2014.04.01
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초록

연소 시, 입자상 물질에 대한 HTPB/AP 계열 고체추진제의 음향특성을 정량화하기 위해서, Pulsed DB/AB T-burner 실험을 수행하였다. 추진제 전면에서 동시 점화를 위해, 대상 고체추진제보다 연소속도가 빠른 다른 고체추진제를 대상 추진제 앞면에 부착하였다. 다량의 알루미늄이 포함된 고체추진제에서는 T-burner 내부에서 만들어진 압력섭동에 의한 음향학적 불안정성이 매우 빠르게 감쇠되었고, 반대로 알루미늄이 포함되지 않은 고체추진제에서는 상대적으로 매우 느리게 감쇠함을 확인하였다. 본 연구에서는 음향학적 특성값들을 정량화하였고, 이를 통해 연소응답 특성을 계산하였다.

T-Burner tests of an Al/HTPB propellant in conjunction with a Pulsed DB/AB Method were conducted to find an acoustic amplification factor. Aluminum-free and aluminum-heavy propellants were examined. Instant surface ignition was successfully made by the use of a supplementary propellant of fractionally higher reaction rate. With the presence of higher aluminum concentration in the propellants, the pressure perturbations were promptly damped down and the pressure fluctuations were no longer dispersive. Addition of aluminum particles into the propellant was advantageous for stabilizing pressure-coupled unstable waves.

키워드

참고문헌

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