• Title/Summary/Keyword: 고체연료램젯

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Effects of Additives and Ignition Support Material on HTPB Fuel Grains for Solid Fuel Ramjet (고체연료 램젯용 HTPB 연료그레인에 첨가제와 점화보조제가 미치는 영향)

  • Jung, Woosuk;Baek, Seungkwan;Jung, YeonSoo;Kwon, Taesoo;Park, Juhyun;Kim, Incheol;Kwon, Sejin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.957-967
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    • 2017
  • Firing test of the fuel grain for solid fuel ramjet with additives and ignition support material was conducted. Fuel grain consist of HTPB mixed with AP particle 15 wt.%, Boron particle 5 wt.%. To cause the short ignition delay, ignition support consist of $NC/BKNO_3$ and composite propellant was coated to the fuel grain. An oxidant gas having a controlled temperature, pressure and oxygen composition close to the air condition in the ramjet combustor was supplied using the Ethanol blended $H_2O_2$ gas generator. Gas was set to flow at a mass flow rate of 150 g/s and mass flux of $200kg/m^2s$ in the grain port. Through the test, ignition support operated well and ignition delay of 0.5. During the test, stable chamber pressure with 8 bar and high combustion efficiency of 0.86 was confirmed.

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Ignition of Fuel-rich Propellant Coated with Ignition Support Material in the Ramjet Combustor Condition (램젯 연소실 조건에서 점화보조제가 도포된 Fuel-rich 추진제의 점화)

  • Jung, Woosuk;Baek, Seungkwan;Kim, Youngil;Kwon, Taesoo;Park, Juhyun;Kwon, Sejin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.4
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    • pp.79-88
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    • 2017
  • Ignition test of the fuel-rich propellant coated with ignition support material in the ramjet combustor condition was conducted. Ignition delay and flame holding was measured. Fuel grain consist of HTPB mixed with AP particle 15 wt.%, Al particle 5 wt.%. To cause the short ignition delay, ignition support consist of $NC/BKNO_3$ and composite propellant was coated to the fuel grain. Ethanol blended $H_2O_2$ gas generator control the temperature, pressure, $O_2$ concentration in the oxidizer gas in the air. Gas is supplied with mass flux of $200kg/m^2s$. Through the test ignition support operated well and ignition delay of 0.6 second and the Flame was sustained.

The Study of Aerodynamic Characteristics of Ram-jet with Different Intake (서로 다른 램제트 흡입구에 따른 공기역학적 특성 연구)

  • Park, Soon-Jong;Park, Jong-Ho
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.6
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    • pp.9-16
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    • 2010
  • The SFRJ(Solid Fuel Ram-Jet) propulsion is attractive for projectiles because of the combination of high propulsive performance and low system complexity more than conventional projectiles. The Objective of this research was to characterize the inlet aerodynamic characteristics (center-body & pitot type) in SFRJ. Diffuser static pressure & combustion chamber pressure was tested and the AoA was changed $0^{\circ}$ and $4^{\circ}$ at Mach number of 3.0 for performance estimate. The performance study of inlet was carried out with the Schlieren system and Supersonic cold-flow system. Under mach 3.0, the center-body showed twice higher total pressure recovering ratio than the pitot type. A Computational fluid dynamic solution is applied internal flow of inlet and the solutions are compared with experimental results.