• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.203-207
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• 2007

In this study, the combustion characteristics of HTPB was studied in hybrid propulsion system. In this experiments HTPB was used as fuel, GOX was used as oxidizer. The mass flow rate of GOX was controlled by the several chocked orifices that have different diameter, and the oxidizer supply range was $13.8{\sim}42.7g/sec$. The experimental result of HTPB was compared with the other studies of HTPB, and the combustion performance of HTPB was analyzed with that of PE. As a result, the homing rate and efficiency of HTPB as fuel were better than that of PE in the same hybrid motor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.413-416
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• 2005

The study has been performed on the improvement of bonding process and bond strength of HTPB propellant and liner using a polymeric curative. In case of liner using polymeric curative prepared from reaction of HTPB and TDI, migration of curative was decreased at bond interface. So EPDM insulation sanding and Desmodur RE coating process could be omitted in motor case preparation and bond strengths between the HTPB propellant and liner were increased. Also deterioration phenomena of bond strength could not be observed in accelerated aging test.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.110-114
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• 2006

The study has been performed on the improvement of bonding process and bond strength of HTPB propellant and liner using a polymeric curative. In case of liner using polymeric curative prepared from reaction of HTPB and TDI, migration of curative was decreased at bond interface. So EPDM insulation sanding and Desmodur RE coating process could be omitted in motor case preparation and bond strengths between the HTPB propellant and liner were increased. Also deterioration phenomena of bond strength could not be observed in accelerated aging test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.279-282
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• 2008

The AP/HTPB composite propellant is a common choice for solid rocket propulsion. The externally heated rocket via fires, for instance, can cause the energetic substance to ignite, and this may lead to a thermal runaway event marked by a severe explosion. In order to develop preventive measures to reduce the possibility of such accidents in propulsion systems, we investigate the ignition and initiation properties of AP/HTPB propellant.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.148-153
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• 2017

During natural ageing of HTPB propellant undergoes a series of slow physico-chemical degradation reactions. By using accelerated ageing conditions it is possible to simulate the material behaviour at different time-temperature conditions especially focused on the in-service conditions. Ageing behaviour of HTPB propellant were investigated using HFC(Micro-Heat Flow Calorimeter) is universal technique for measuring the rate of slow chemical and physical processes in long-term storage.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.59-65
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• 2018

During natural aging, hydroxyl-terminated polybutadiene(HTPB) propellant undergoes a series of slow physico-chemical degradation reactions. By using accelerated ageing conditions it is possible to simulate the material behavior at different time-temperatures focusing on in-service conditions. Aging behaviors of HTPB propellant are investigated using HFC(heat flow calorimeter), a universal technique for measuring the rate of slow chemical and physical processes in long-term storage.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.1
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• pp.29-34
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• 2011

Hydroxyl terminated polyether(HTPE) propellants have been developed recently as possible replacements for HTPB/AP propellants currently used in a number of tactical rocker motor. As analyzing friability of HTPE and HTPB propellants in this study, 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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• 2017.05a
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• pp.504-507
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• 2017

The polybutadiene-based HTPB used as the propellant main binder influences the curing reaction rate of the binder and propellant depending on the synthetic batch. The properties of HTPB synthesized in different batches were analyzed and applied to propellants to evaluate the curing reaction rate and mechanical properties. Finally this reaction can also affect mechanical properties of propellant. And the results suggest that proper degree of curing reaction is necessary to obtain better mechanical properties of propellant.

• 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.