• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.11a
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• pp.193-198
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• 1996

고연소속도 HTPB/AP 추진제를 얻기 위하여 현재 각광받고 있는 3종의 철화합물 연소촉매를 선정하여 연소속도 증진효과와 기계적 특성, 공정성 및 노화특성에 미치는 영향을 검토하였다. 사용한 철 화합물은 HTPB 프리폴리머에 silicone-ferrocene이 그라프트된 $BUTACENE^$\circledR$$ 과 결합제 역할을 하는 acylaziridinyl ferrocene(AAF), 그리고 입자크기가 30nm인 $NANOCAT^$\circledR$$ superfine iron oxide(SFIO)이었다. 이들 철 화합물을 추진제에 적용한 결과 공정성의 경우 $BUTACENE^$\circledR$$ 은 혼합점도가 높았으나 pot life의 감소는 없었으며 AAF와 SFIO는 혼합점도는 비교적 낮은 반면 pot life가 현저히 감소하는 경향을 보였다. 추진제의 노화거동은 연소촉매를 사용하지 않았을 때보다 저하되었으나 metal deactivating 산화방지제인 $PRO-TECH^$\circledR$$ 과 함께 사용할 경우 공정성 및 노화특성 모두 바람직한 수준으로 향상되었다. 기계적 특성은 SFIO를 제외하고는 저하되었으며 $BUTACENE^$\circledR$$ 은 프리폴리머로서, AAF는 결합제로서의 기능이 다소 미흡하였다. 한편 연소촉매의 함량에 따른 촉매효과는 AAF>SFIO>$BUTACENE^$\circledR$$ 순이었고 철 함량 측면에서는 AAF>$BUTACENE^$\circledR$$ >SFIO 순이었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.460-463
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• 2011

Different kinds of solid rocket motors manufactured for various aim have their own shelf life. So they must be done away if not used. In general, ammonium perchlorate(AP) has used in the process of solid rocket motors, which is environmental pollutant. Out-burning and out-detonation were usual in the past, but they polluted the surrounding environment and raised safety issues. As an alternative to resolve these, water-washout process to separate the propellant from rocket motors and an eco-friendly way for recovering AP are studied in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.04a
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• pp.205-211
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• 1997

최근 유도무기 분야에서 많이 사용되고 있는 가스발생기는 온도가 낮고, 독성이나 부식성이 없는 연소 가스를 요구하고 있기 때문에 산화제로 Ammonium Nitrate(AN)를 주로 사용하고 있다. 그러나 순수한 AN은 온도에 따라 상이 변하는 단점이 있기 때문에 Phase Stabilized Ammonium Nitrate(PSAN)을 사용하고 있으며, 일반적으로 PSAN은 AN과는 다른 연소특성을 갖는다. 본 연구에서는 가스발생기용 추진제의 조성을 연구하면서, 상안정제로 $KNO_3$와 $KCIO_4$을 사용하여 자체적으로 제조한 PSAN들과 ZnO=3%인 PSAN을 사용하여 얻은 추진제의 연소특성을 고찰하였고, 연소촉매를 사용하거나 RDX나 소량의 AP를 사용하여 보다 다양한 연소속도를 갖는 추진제를 제조할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.4
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• pp.363-368
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• 2010

In the solid rocket propellant combustion, the dynamic phase change from solid to liquid to vapor occurs across the melt layer. During the surface burning, liquid and gas phases are mixed in the intermediate zone between the propellant and the flame to form micro scale bubbles. The known thickness of the melt layer is approximately 1 micron at $10^5$ Pa. In this paper, we present a model of the melt layer structure and the dynamic motion of the melt front derived from the classical phase field theory. The model results show that the melt layer grows and propagates uniformly according to exp(-1/$T_s$) with $T_s$ being the propellant surface temperature.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.147-150
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• 2003

The purpose of this research was to develope components of micro solid propellant thruster. Micro solid propellant thruster had four basic components: combustion chamber, nozzle, solid propellant and micro heater for ignition. A performance of micro heater and characteristic of solid propellant was investigated. Micro heater was fabricated by conventional MEMS process and Platinum layer was used for heating element. Effect of geometry parameters on micro heater was tested. The temperature responses of heater with respect to each parameters was compared for a given electrical power. The characteristic of solid propellant(HTPB/AP) was investigated to obtain burning velocity in small chamber. Additionally, a capacity of filling propellant with high viscosity in small chamber was checked to guarantee for the micro fabrication.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.307-310
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• 2005

This Study was performed for the Insensitive Munition Technology Program contract between Roxel and ADD. Two Slow Coo-off(SCO) tests and One fast Cook-off(FCO) test have been made based on MIL-STD-2105C. SCO and FCO tests were made in order to evaluate the behaviour of the hybrid rocker motor with insensitive igniter and two types of propellants of which burning rates were 9.8 mm/s and 21.2 mm/s @ 7 MPa each other. The Reaction level of the two rocker motors to SCO test was classified as type IV and that of FCO test was classified as type V.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.175-178
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• 2008

A Numerical Simulation which uses preconditioning algorithm to examine unsteady combustion processes for the AP/HTPB propellant with a converging-diverging nozzle has been compared with experimental data for solid rocket motor. To analysis reacting flow of solid rocket motor, unsteady pressure, temperature contour was simulated by grid moving of propellant.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.4
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• pp.69-76
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• 2015

Recently, environmental sustainability of the transitional explosives and propellants is an issue of growing importance in energetic materials. For examples, ammonium perchlorate(AP) as an solid propellants oxidizer could create a poisonous gas and atmospheric pollutions, such as HCl. Among the several oxidizers, hydrazinium nitroformate(HNF) is an effective candidate substance for eco-friendly oxidizer, which has high density, pressure index, and less smog generating property during combustion for the Divert and Attitude Control System(DACS). This study was confirmed a synthesis through various conditions, was performed for the essential data of solubility the crystallization process. Also, crystallization process such as cooling, drowning-out and sonication were performed.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.6
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• pp.76-82
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• 2016

Recently, environmental sustainability of the transitional explosives and propellants is an issue of growing importance in energetic materials. For examples, ammonium perchlorate(AP) as an solid propellants oxidizer could create a poisonous gas and atmospheric pollutions, such as HCl. Among the several oxidizers, hydrazinium nitroformate(HNF) is an effective candidate substance for eco-friendly oxidizer, which has high density, pressure index, and less smog generating property during combustion for the thrust control system. This study was controlled the size distribution and shapes through various conditions. Length and diameter ratio(L/D) of crystals has below 1 : 3, and the particle size was two types of $200{\mu}m$ and $50{\mu}m$.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.05a
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• pp.85-92
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• 1995

HTPB/AP/Al이 기본 조성인 ADP 302 혼합형 추진제를 대상으로 4종의 금속선(Ag, Cu, Al, Ni-Cr)을 삽입하여 금속선 직경(0.1mm~0.8mm)별로 압력에 따른 금속선과 인접한 추진제의 연소 속도($r_w)를 측정하여 금속선 삽입 추진제의 연소 속도 증가비($r_w$/$r_sb$)와 압력 지수( n )의 변화를 고찰한 결과 금속선 종류에 따른 연소 속도 증가비($r_w$/$r_sb$)는 Ag> Cu>Al>Ni-Cr선을 삽입한 추진제의 순으로 나타났고 금속선의 열확 산 계수의 크기순과 일치하였다. Buckingham $\pi$ 이론을 적용한 무차원 해석으로부터 실험식을 구하여, 이 실험식에 의해 계산된 ($r_w)와 실험으로부터 얻어진 ($r_w)를 서로 비교하여 본 결과 잘 부합됨을 알 수 있었다. 또한 금속선 수에 따른 추진제 그레인의 연소 면적을 해석적으로 계산하여,($r_w$/$r_sb$)가 2, 3, 4, 5 배로 증가함에 따른 시간에 따른 연소 면적 증가비의 변화를 금속선 수에 따라서 비교하여 본 결과 정상 상태에서의 그레인의 연소 면적의 증가비($A_b$/$A_0$)는 금속선에 인접한 추진제의 연소 속도 증가비($r_w$/$r_sb$)와 일치했으며, 정상 상태의 연소 면적 증가비는 삽입된 금속선의 수와는 무관하며 정상 상태에 도달하는 시간에만 영향을 주는 것으로 나타났다.