• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.11a
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• pp.15-15
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• 1997

본 연구는 전방점화 방식(the head-end ignition)을 채택하고 있는 composite 고체 추진기관(구룡 1모타)을 이용하여 후방점화 방식(the after-end ignition)에 의한 점화 가능성을 검토하였으며, 점화 방식 차이에 따른 추진기관의 초기 연소거동의 차이점을 고찰하고자 한 실험 연구로서, 후방 점화장치를 설계·제작하여 지상연소시험을 수행하였다. 점화장치는 착화장치(initiation system)와 에너지 방출장치(energy release system), 구조물(Hardware)로 구성되는데, 착화장치는 기존의 K2 squib를 사용하였고, 에너지 방출장치는 FRP튜브에 MTV pellet 점화제를 사용하였으며, 점화기를 후방에 부착시키는 방법으로는 flexible finger 형태의 locking sleeve를 설계하여 노즐목에 고정하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.149-152
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• 2009

A pyrostarter is a sort of gas generator, which supplies the energy to drive turbines by the combustion gas of a solid propellant charged internally. The igniter of the pyrostarter should guarantee the ignition reliability expecially for the solid propellant with a low fame temperature. For the development of the igniter, several closed bomb testes have been performed to decide several design parameters to get a sufficient chamber pressure build-up for the ignition. Moreover, as a result of the firing testes with pyrostarters, the ignition reliability have been verified and the amount of igniter propellants has been reviewed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.213-216
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• 2009

In order to see the flame behavior in the gas turbine combustor, combustion test was performed by using sector combustor. Ignition test with torch ignition system was carried out at the various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with fixed air mass flow rate. In the test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet air velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity.

• Fire Science and Engineering
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• v.18 no.1
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• pp.18-23
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• 2004

This paper describes the minimum ignition limits for propane-air 5.25 Vol.% mixture gases in low voltage inductive circiuts. The improved effects on the ignition limit are studied by parallel safety components(resistors) for propane-air 5.25 Vol.% mixture gas in low voltage inductive circuits. The experimental devices used in this test are the IEC type spark ignition test apparatus. The minimum ignition limits are controlled by the values of current in inductive circuit. Energy supplied from electric source is first accumulated at the inductance, it's extra energy is working as ignition source of the explosive gas. The improved effects on the ignition limit are respectively obtained as the maximum rising rate of 330% by composing parallel circuits between inductance and resistor as compared with disconnecting inductance with the safety components. The more values of inductance increase the higher improved effects of ignition limit rise. The less values of resistor the higher improved effects of ignition limit rise. It is considered that the result can be used for not only data for researches and development of intrinsically safe explosion-proof machines which are applied equipment and detectors used in dangerous areas but also for datum for its equipment tests.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.4
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• pp.11-17
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• 2011

In order to see flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65 m/s.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.153-159
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• 2010

In order to see the flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at the various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In the test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65m/s.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.72-76
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• 2010

To research and develop a high performance injector for LRE, it needs not only cold flow test, but also investigations of combustion performance, optimization of cyclogram and thermo-fluid dynamical characteristics of combustion flow field through hot-fire test. In this study, hot-fire test of LOX-CH4 coaxial swirl injector has been carried out using lab-scale hot fire test stand which can supply and control cryogenic propellant. Ignition and continuous combustion for LOX-$GCH_4$ propellant of 0.19 kg/s total mass flowrate and 2.80 O/F Ratio was achieved through cyclogram optimization. The mean combustion chamber pressure and thrust were measured as approximately 1.43 MPa and 38.7 kgf respectively.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.1
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• pp.98-106
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• 2022

To develop reliable dual pulse rocket motor, vacuum ignition performance at high altitude and design stability for rupture pressure of the Pulse Separation Device(PSD) are required. In this study, rupture pressure analysis method for the membrane type PSD of the dual pulse rocket motor was developed. The PSD rupture pressure formulation was derived from strain-pressure relationships. The PSD vacuum rupture test apparatus and the PSD 1 second vacuum ignition test apparatus were developed, which can simulate the high altitude vacuum environment. Rupture pressure of PSD was analyzed by conducting the PSD vacuum rupture test, and design values of PSD were derived. Finally, vacuum ignition performance and rupture pressure of the designed PSD were validated with PSD 1 second vacuum ignition test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.13-13
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• 2000

일반적으로 고체추진 로켓 모타의 개발단계 때 공통적으로 수행되는 주시험(main test)으로는 추력, 압력, 회전률 등의 성능측정을 하기 위한 정적연소시험(static firing test), 내부 정수압(hydrostatic pressure)에 의한 폭발 압력 시험, 연소중이나 연소 후 케이스에 대한 굽힘 강성 시험, 이외에 노화 시험, 환경시험 등이 요구된다. 그러나 신궁과 같은 휴대용 대공 시스템의 추진기관 개발의 경우에는 사수를 보호하기 위해 여러 가지 안전장치들이 설계되고, 이러한 장치들의 성능에 대한 요구 조건들을 확인하기 위한 특수시험(specific test)들이 필요하게 된다. 이러한 특수시험을 위한 각종 시험대들을, 위에서 언급한 주시험을 위해 사용되는 정적시험대(static test bench)들과 구분하기 위해 동적 시험대(DTB : Dynamic Test Bench)라고 한다. 본 연구에서는 신궁 추진기관의 사출모타 점화에서 비행모타 점화에 이르는 일련의 비행절차를 확인하기 위한 동적 시험대 설계 및 제작, 계측장치 구성 및 데이터 획득 방법 등에 관한 내용을 소개하며, 동적 시험대에서 수회에 걸쳐 수행된 동적 시험 결과를 분석/정리하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.227-230
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• 2008

Igniter system of Solid Rocket Motor is classfied as Forward-end type and After-end type. Forward-end type is used for sustentation of combustion pressure by nozzle plug. But After-end type is used for sustentation of combustion pressure by igniter mount. Igniter Mount is assembled on nozzle throat. Igniter mount holds combustion pressure and igniter release energy. A study has qualificated result of Dynamic behavior for After-end igniter mount of Static Firing Test and Finite element method.