• Journal of the Korean Society of Safety
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• v.13 no.4
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• pp.137-141
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• 1998

The combustion instability of a rocket motor can be predicted by the linear stability analysis. The most important input data in this analysis is the combustion response function of the solid propellant. In many cases, it is very difficult to measure the function. But, in that case, the combustion response function can be theoretically evaluated by properties of the propellant. In this study, the theoretical values were compared with measured values by T-burner. Data are relatively so well agreed that theoretical values are enough to be used in linear stability analysis of the rocket motor using a newly developed propellant.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.4
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• pp.114-122
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• 2000

Bullet impact tests for solid rocket motor were performed and its results wert described. Two motors were made of composite and steel for case material, respectively and their reactions to the bullet impact were compared. Throughout the tests it had been tried to setup the procedure of bullet impact test and criteria of the judgment for the reactions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.201-212
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• 2012

In general solid propulsion offers cost effective, large thrust capabilities comparing to the liquid propulsion which offers high specific impulse and restart capabilities. Therefore solid propulsion is well fitted for the first stage and boosters. BBL approach has been studied for the launch vehicle because of cost effectiveness, limited development time and low risk. Using of the carbon fiber epoxy resin in the solid rocket motor case is expanded, and specially high strength fibers are more attracted since its inert mass reduction.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.183-186
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• 2008

Both structural analysis and hydraulic test have been conducted to confirm the burst characteristics of filament wound solid motor case. Failure criteria have been defined with bursting above 150% of MEOP and failure in the cylinder. The results of analysis showed that filament fiber in the cylinder should be broken at about 2088psig. From a hydraulic test the same failure mode and the level of 2200psig of burst pressure have been proved. With these results, it is verified that a filament wound case meets burst requirements.

• Journal of the Korean Society for Nondestructive Testing
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• v.32 no.4
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• pp.401-409
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• 2012

Ultrasonic testing are far superior to other nondestructive tests for detecting the disbond interface which occurred in adhesive interface. However, a solid rocket motor consisting of a steel case, rubber insulation, liner, and propellant poses many difficulties for analyzing ultrasonic waves because of the superposition of reflected waves and large differences in acoustic impedance of various materials. Therefore, ultrasonic tests for detecting the disbond interface in solid rocket motor have been applied in very limited areas between the steel case and rubber insulation using an automatic C-scan system. The existing ultrasonic test cannot detect the disbond interface between the liner and propellant of a solid rocket motor because most of the ultrasonic waves are absorbed in the rubber material which has low acoustic impedance. This problem could be overcome by analyzing the resonance frequency from the frequency spectrum using the ultrasonic resonance method. In this paper, a new technique to detect the disbond interface between the liner and propellant using ultrasonic resonance characteristics is discussed in detail.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.77-80
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• 2006

Insensitive Munitions(IM) of solid propulsion system are defined as munitions that fulfil the performance and operational requirements, but will minimize the violence of a reaction when subjected to inadvertant stimuli. It should be clear that the reaction violence of rocket motor subjected to thermal stimuli can be mitigated by reducing confinement prior to propellant reaction. Devices designed to do this by venting the rocket motor case are commonly referred to as mitigation devices. The objective of this paper is to introduce the technical information related to the pyrotechnic mitigation devices for insensitive munition of solid rocket motor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.278-281
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• 2004

The purpose of this paper is to show a reliable analytical method to predict the deflections of F/W Composite Motor Case. Structural analysis and testing of a Carbon/Epoxy Composites Motor Case for Pressure Loadings were performed. This paper presents the development of 3-D layered axi-symmetric solid element for finite element analysis. Finite element analyses were preformed considering fiber angle variation in longitudinal and thickness direction by ANSYS. The analytical results agree well with experimental results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.203-206
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• 2008

In this study, we focused on development of the adhesive insulator using the case for solid rocket motors. Material of insulator used unvulcanized rubber based on EPDM/kevlar. In case of front insulator, preforms was made by using hot press molding, and then modified nylon film was inserted between two preforms for boots manufacturing. Rear insulator included cylinder part was embodied by only one mold with special designed and manufactured shape in the process. Boots part of rear insulator was obtained by cutting machine with hard-metal cemented carbide.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.5
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• pp.97-107
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• 2012

In general, solid propulsion offers cost effective, large thrust capabilities comparing to the liquid propulsion which offers high specific impulse and restart capabilities. Therefore, solid propulsion is well fitted for the first stage and boosters. Building Block Launcher(BBL) approach has been studied for the launch vehicle because of cost effectiveness, limited development time and low risk. Using of the carbon fiber epoxy resin in the solid rocket motor case is expanded, and specially high strength fibers are more attracted since its inert mass reduction.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.257-262
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• 2009

Elastic-Plastic structural analysis was performed to evaluate structural characteristic and integrity for rocket motor case of solid propulsion system. The structural analyses were compared and evaluated using the simplified 2-D axisymmetric model and 3-D full model for rocket motor case with torispherical dome type. And pre-tension load for bolt model was considered in structural analysis. The results of displacement and stress for the simplified 2-D axisymmetric model and 3-D full model were in an good agreement with each other. Therefore, the simplified 2-D axisymmetric model for rocket motor case was recommended to verify quickly the structural integrity and save the modeling and calculating time in initial design stage. Also, the structural characteristic and integrity for rocket motor case according to 5 dome types was evaluated to select the optimal dome shape.