• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1997.11a
• /
• pp.14-14
• /
• 1997

추진제의 노화 못지 않게 점화제의 노화도 추진 기관 성능에 큰 영향을 미칠 것으로 예측된다. 따라서 10년 이상 경과된 활성 모터에서 점화기를 분해하여 노화에 의한 점화제의 성능 변화를 알아보았다. 분석에 사용한 점화제는 II-D Bi-Convex형상의 B-KNO$_3$ 펠렛으로 열량, 자동 점화온도, 기계적 물성의 변화를 관찰하였고, 밀폐 용기(Closed bomb)에서 연소시험을 통하여 노화에 따른 점화알약의 압력변화를 측정하고 이론 값과 비교하였다. 또한 비활성 모타를 이용한 연소시험으로 점화기의 점화지연시간, 최대 압력, 최대 압력 도달시간 등을 측정하고 이론식과 비교하여 노화에 의한 변화를 관찰하였다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.3
• /
• pp.90-96
• /
• 2018

This study investigated the manufacturing process and characteristics of $BKNO_3$ (Boron Potassium Nitrate) as a pyrotechnic propellant that is commonly used in the aerospace, defense, and automobile industries. The solid mixture was composed of oxidizing agent, fuel, and binder. Evaporation process was used to uniformly mix the raw materials. The optimal ratio of composition was designed through the CEA program analysis of the material characteristics and thermal responses. Further the size, shape, sensitivity, and calorimetry characteristics were studied.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.433-439
• /
• 2017

This research investigates the manufacturing process and characteristics analysis of $BKNO_3$ (Boron Potassium Nitrate) as pyrotechnic are commonly found in the aerospace, defense, and automotive industries. A solid pyrotechnic mixture is composed of an oxidizing agent, fuel, and binder. Precipitation process was used to uniformly mix the raw material. Through the analysis of the material characteristics and thermal response is designed optimum ratio by NASA CEA program. It was compared by performing the evaluation of these size/shape/sensitivity/calorimetry characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1036-1037
• /
• 2017

This study investigated the aging reactions of three kinds of igniters(BKNO3, THPP, ZPP). The life-time of igniter depends on oxygen and moisture in the air. For example, Magnesium contained in the $BKNO_3$ reacts with oxygen and water to form oxide and hydrate. This reaction has an adverse effect on ignition reaction and could be information to analyze aging. Thermodynamic calculation could interpret the aging reaction by calculating flame temperature applying several variables(initial temperature, composition, etc.). If combustion is not completed because of aging igniters, flame temperature will be formed at a low range. The result of this research is expected to support the analysis of igniters aging reactions.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.21 no.4
• /
• pp.79-88
• /
• 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.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.19 no.1
• /
• pp.1-8
• /
• 2015

Micro igniter on the glass membrane for MEMS thruster was developed. The stability of the micro igniter by using a glass membrane with a thickness of tens of microns was improved. The micro igniter was fabricated by anisotropic wet etching of photosensitive glass and deposition of Pt/Ti for electric heat coil. The solid propellant was loaded into the propellant chamber without an especial technique due to the high structural stability of the glass membrane. Ignition tests were performed successfully. The minimum ignition delay was 27.5 ms with an ignition energy of 19.3 mJ.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.3
• /
• pp.8-13
• /
• 2018

Zirconium potassium perchlorate(ZPP) is an igniter composed of potassium perchlorate as an oxidizing agent and zirconium as a fuel with a Viton binder. ZPP has been used to provide an ignition source in the aerospace, propulsion, and automotive industries. This study investigates the manufacturing process and characteristics of ZPP, such performance and shape/calorimetry/pressure characteristics with respect to pyrotechnic mechanical device(PMD). During the production of ZPP, the mixing process was designed to produce uniform particle size and shape by mixing the raw materials at high speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.445-450
• /
• 2017

ZPP(Zirconium Potassium Perchlorate) is an igniter composed of potassium perchlorate as oxidizing agent and zirconium as fuel with a Viton binder. ZPP is used to provide ignition in the aerospace, propulsion, automotive industries. This research is investigated for the manufacturing process and characteristics analysis of the ZPP such as the performance and shape/calorimetry/pressure characteristics of the ZPP on PMD(Pyrotechnic Mechanical Device). During the production of ZPP, the mixing process was designed so that the ZPP could be produced in uniform particle size and shape by mixing the raw materials at high speed.

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

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.130-133
• /
• 2009

The sequence of the propellant supply is very important for the reliable and safe operation of a LRE combustion test. So combustion performance tests were performed to find an optimum test sequence by changing supply time of propellants and purge gas in the moment of ignition and extinction. The liquid rocket engine consisted of a catalytic ignitor and six swirl-coaxial injectors which used hydrogen peroxide and kerosene. Conclusively, an optimum sequence was found for stable combustion in the moment of ignition and extinction.