• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.4
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• pp.21-27
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• 2017

In this paper, in order to control the burning rate and pressure exponent of HTPB/AP/Al based propellant for the improvement of performance, the effect of the size ratio of AP particles and various contents of Butacene as burning catalyst on combustion properties was investigated. In the propellant formulation with both $28{\mu}m$ Al of 23% and Butacene of 3%, the burning rate and pressure exponent were increased with increasing the contents of $9{\mu}m$ AP particles. And the burning rate was increased with increasing the contents of Butacene with showing the relatively low pressure exponent in the propellant containing Butacene. However, the significant variations of pressure exponent by contents of Butacene were not observed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.75-78
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• 2005

The present work has been studied to investigate the effect of formulation on friability of HTPB/AP propellants including Butacene and $Cr_{2}O_3$. The mechanical properties and burning rate of the propellants were measured using Inston tensile tester and strand burner, respectively. Friability was calculated by shot-gun and closed bomb test. The result showed that friability was higher, as the content of Butacene or AP $6{\mu}m$ in the propellant formulations was increased.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.9-17
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• 2002

This Study is to investigate 8 composite propellants including Butacene and ${Bi_2}{O_3}$ by Shotgun/RQ Bomb test. Burning rate and mechanical properity are known to be major factors in determining the deflagrability of propellant. Propellant including over 5.5% Butacene(Ferrocene grafted HTPB) burned out over 135 m/s of impact velocity during Shotgun/RQ Bomb test. It was blown that Butacene was very sensitive material under high velocity impact. In the test results, propellants under 25mm/s in burning rate at 1500 psia could meet the requirements for IM of UN Test Series 7c(ii). Propellant deflagrabillity depends on burning rate at performance in the results of the present.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.2
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• pp.40-45
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• 2005

In the present work, the effect of formulation on friability of HTPB/AP propellants including Betacene and $Cr_2O_3$ has been studied. The mechanical properties and burning rate of the propellants were measured using Inston tensile tester and strand burner, respectively. Friability was calculated from shot-gun and closed bomb test data. The result showed that friability was higher, as the content of Butacene or AP $6{\mu}m$ in the propellant formulations was increased.

• 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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• 2009.05a
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• pp.169-172
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• 2009

In this study, the current researches and the developing trend of the high burning rate solid propellants were briefly introduced and the effects of burning rate modifiers in the propellants on the combustion properties were reviewed. At the same time, bis(ethylenediamine)copper perchlorate(BECP) has been prepared as a burning rate modifier, and the burning characteristics were investigated in Butacene/AP propellants. The results showed that the metal complex, BECP, can increase remarkably the burning rate of high burning rate Butacene/AP propellants.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.508-512
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• 2017

In this study, we carried out the study on the combustion characteristics of HTPB/AP propellants with Al and Zr as fuel metal in order to develop the solid propellant with high burning rate. The major combustion characteristics of propellant were investigated as measuring of the burning rate and pressure exponent, and the HTPB/AP solid propellants were prepared with introducing Butacene as burning rate catalyst for the enhancement of burning rate. The propellant with Al and Zr was demonstrated the improvement of propellant performance and combustion characteristic.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.61-65
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• 2005

In HTPB/AP propellants, zirconium(Zr) addition to formulation was shown to be less specific impulse than aluminum(Al) by the theoretical calculation because of the lower flame temperature and higher molecular weight of Zr oxide. It was found that the burning rate was faster with the finer size of Zr and the more content of $2{\mu}m$ Zr the faster burning rate is in HTPB/AP/Zr propellants caused by the more conduction energy transfer from Zr flame to the burning surface. Also the burning rate of HTPB/AP/Zr propellant could be reduced by addition of 150nm Al, depending on AP size distribution in formulation with Butacene and $1{\mu}m$ AP.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.2
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• pp.9-16
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• 2005

Zirconium(Zr) addition to formulation of HTPB/AP propellants, was shown to be less specific impulse than aluminum(Al) by the theoretical calculation because of the lower flame temperature and higher molecular weight of Zr oxide. It was found that the burning rate was faster with the finer size of Zr and the more content of $2{\mu}m$ Zr the faster burning rate is in HTPB/AP/Zr propellants caused by the more conduction energy transfer from Zr flame to the burning surface. Also the burning rate of HTPB/AP/Zr propellant could be reduced by addition of 150nm Al, depending on AP size distribution in formulation with Butacene and $1{\mu}m$ AP.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.18-25
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• 2017

The study for the combustion characteristics of propellants for nozzleless boosters was carried out. The metal fuels of Al and Zr were introduced into solid propellant formulations in order to enhance the density-specific impulse and the high burning rate with low pressure exponent was investigated as the major combustion characteristic of propellant to design nozzleless boosters. The burning rate of Zr-containing propellant was higher than Al-containing propellant and, $13{\mu}m$ Zr-containing propellant exhibited the burning rate of 35 mm/s (at 1000 psi)and pressure exponent of 0.3282. The benefit of using Al and Zr-containing propellant into nozzleless boosters was demonstrated in these results.