• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.229-232
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• 2006

Two novel synthetic route proposed for Hydro-Terminated Poly(EO-ran-THF) and tri-block(PEC-PTHF-PEG) copolymer by cationic ring-opening polymerization of tetrahydrofuran(THF) and ethylene oxide(EO) and just by polymerization of EO on poly-THF, respectively. Polyurethane was synthesized from random and tri-block HTPE using N-100/IPDI mixture as curing agent, and TPB(Triphenylbismuth) as catalyst. The mechanical properties of resultant polyurethane after mixing with various ratio of isocyanate was also investigated. Finally, the post treatment process of HTPE based on amount of catalyst used in the synthesis was studied, to evaluate the optimum curing condition for the polyurethane propellant binder.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.221-226
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• 2008

Novel synthetic routes were proposed for hydroxy-terminated Poly(EO-co-THF) by Cationic ring-opening copolymerization of Tetrahydrofuran(THF) and Ethylene oxide(EO). It was carried out using Boron trfluoride tetrahydrofuranate($BF_3$ THF complex) as catalyst in the presence of 1,4-butandiol. The resultant products are well-defined linear polyetherpolyol. Polyurethane(TPU) were prepared using resultant polyetherpolyol with IPDI/N-100 as curing agent and TPB(Triphenylbismuth) /MA(Maleic anhydride) mixture as cure catalyst. Mechanical properties of TPU prepared from poly(EO-co-THF) polyol were investigated and compared with polyurethane using ATK HTPE.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.369-372
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• 2010

As analyzing friability of HTPE and HTPB propellants, the following results could be derived. The friability of the tested propellants depended on its binder contents, mechanical property, and burning rate. It was decreased as burning rate was lowered and toughness was increased.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.167-170
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• 2009

Fast cook-off test with rocket motors was performed and characteristics of the results were analyzed. The material of the motor case was carbon epoxy composite. The motor was loaded with HTPE propellants to improve the insensitive munitions characteristics. In the tests, sound pressure and heat flux sensors were used to determine the category of response according to the standard. The reaction response of all of the HTPE motors tested by fast cook-off was judged as Type V burning.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.163-166
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• 2009

Bullet and fragment impact test with rocket motors was performed and characteristics of the results were analyzed. The material of the motor case was carbon epoxy composite. The motor was loaded with HTPE propellants to improve the insensitive munitions characteristics. In the tests, sound pressure and heat flux sensors were used to determine the category of response according to the standard. The reaction response of all of the HTPE motors impacted by bullet and fragment was judged as Type V burning.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.155-158
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• 2009

This study was investigated to know the thermal decomposition and measure the reaction time and temperature by EIDS cook-off test for the propellant ingredients and 2 kinds of HTPE propellants. The thermal analysis of the propellant ingredients used in this study showed that the thermal stability of these materials decreases in the following order : AP > HTPE > AN > BuNENA. In addition, propellant HTPE 002 containing AN showed that an endothermic process at around $125^{\circ}C$ corresponding to the solid`solid phase change($II{\rightarrow}I$) of AN was followed by the exothermic process due to decomposition of BuNENA/AN until $200^{\circ}C$. HTPE 001 and HTPE 001 reacted at around $250^{\circ}C$ and $152^{\circ}C$ each other, and the temperature of them sharply increased at $115^{\circ}C$ from EIDS slow cook-off tests.