• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.65-71
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• 2018

There is no significant difference in the initial viscosity of a propellant applied with yellow iron oxide and red iron oxide. In addition, the thermal decomposition rate of the material with added yellow iron oxide is faster than that with the addition of red iron oxide. Specifically, it was confirmed that the pressure exponent was 18% lower at high temperature and high pressure with yellow iron oxide than with red iron oxide. The initial viscosity was lowest at 71% of the large particle to small particle ratio.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.3
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• pp.81-88
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• 2021

An airbreathing propulsion system of a subsonic cruise missile is mainly composed of a small gas turbine engine, air intake and vehicle's fuel tank. The propulsion system integration work started from engine acceptance test is finally closed by ground functional test of the missile's propulsion section, after some modifications of engine's sub-components, development of engine-related onboard systems, interface analyses, and tests. The whole process and stepwise technologies of this system integration work are described herein.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.2
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• pp.73-82
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• 2001

Technical status and prospect of the subsonic airbreathing propulsion system composed of jet engine for missile application are described herein, including analysis of some present airbreathing missiles. Comprehension on this can be applicable both to know deeply about the same type missiles and to get some basic idea of unmanned air vehicle's and light aircraft's propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.05a
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• pp.177-184
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• 1996

We have developed a polysilicon semiconductor bridge (SCB) igniter which produces a plasma discharge that ignites explosive materials pressed against the bridge. Our experiments have demonstrated that the SCB produces a hot plasma that ignites explosives, when driven with a short, low energy peak. The SCB, a heavily-doped film, typically 100 $\mu\textrm{m}$long by 300 $\mu\textrm{m}$ wide 5 $\mu\textrm{m}$ thick, is 30 times smaller in volume than a conventional bridge. We described the SCB operation and processing, and the requirement of obtaining a plasma discharge in order to ignite the explosive material.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.515-518
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• 2010

This technical paper presents future missile trends and propulsion technologies necessary for the missiles. The views are based on open literature briefings of the United States and internet informations. These informations let domestic incorporations prepare technologies for the future. Political and economical environment has been changing worldwidely. More extensive role is required for the incorporations to increase the economic growth of our country. The incorporations should establish the long term product development strategy of their own to compete with foreign countries.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1997.04a
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• pp.121-129
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• 1997

Wave propagation was studied for an unidirectionally reinforced composite materials. The velocities, the particle directions and the amplitudes of reflected and transmitted waves were obtained. This analysis involves an immersion C-scan procedure. Snell's law was modified to get the velocities of waves. This analysis could be applied to the detection of flaws in a transversely isotropic composite motor case.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.163-167
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• 2017

The service life extension of the missile can reduce the replacement cost of the missile, maintain the combat power, and consist of the lifetime assessment of the shelf-life(energetic) items, the maintenance of the missile and upgrade of the related components. This technology should be developed together with the missile system and advanced sustainedly. It is a converging technology that combines various fields of expertise and long-term experiences and databases.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.343-346
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• 2006

In this study, optimization process is constructed for developing missile MDO framework. The analysis tools which are integrated in the missile MDO framework and data flow between analysis tools are investigated. Using analyzed results, the optimal design scenario is constructed. Then to verify optimal design scenario, missile design problem is made and performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.330-339
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• 2008

Ground-based interceptors(GBI) comprise a major element of the strategic defense against hostile targets like Intercontinental Ballistic Missiles(ICBM) and reentry vehicles(RV) dispersed from them. An optimum design of the subsystems is required to increase the performance and reliability of these GBI. Propulsion subsystem design and optimization is the motivation for this effort. This paper describes an effort in which an entire GBI missile system, including a multi-stage solid rocket booster, is considered simultaneously in a Genetic Algorithm(GA) performance optimization process. Single goal, constrained optimization is performed. For specified payload and miss distance, time of flight, the most important component in the optimization process is the booster, for its takeoff weight, time of flight, or a combination of the two. The GBI is assumed to be a multistage missile that uses target location data provided by two ground based RF radar sensors and two low earth orbit(LEO) IR sensors. 3Dimensional model is developed for a multistage target with a boost phase acceleration profile that depends on total mass, propellant mass and the specific impulse in the gravity field. The monostatic radar cross section (RCS) data of a three stage ICBM is used. For preliminary design, GBI is assumed to have a fixed initial position from the target launch point and zero launch delay. GBI carries the Kill Vehicle(KV) to an optimal position in space to allow it to complete the intercept. The objective is to design and optimize the propulsion system for the GBI that will fulfill mission requirements and objectives. The KV weight and volume requirements are specified in the problem definition before the optimization is computed. We have considered only continuous design variables, while considering discrete variables as input. Though the number of stages should also be one of the design variables, however, in this paper it is fixed as three. The elite solution from GA is passed on to(Sequential Quadratic Programming) SQP as near optimal guess. The SQP then performs local convergence to identify the minimum mass of the GBI. The performance of the three staged GBI is validated using a ballistic missile intercept scenario modeled in Matlab/SIMULINK.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.3
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• pp.19-28
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• 2000

In general the data such as thrust, pressure, temperature and combustion time are measured in developing the propulsion system of solid rocket motor through static firing test. But in the case of personal surface to air missile there are required a severe safety specifications in order to eliminate gunner hazard from the exhaust plume of motors. The safety requirements lead to the design of separation device and safety igniter device. The dynamic firing test for the designed two devices should be conducted under the flight environmental conditions to verify the requirements compliance. In this study the technique for dynamic firing test of propulsion system of personal surface to air missile is proposed and the method to design the dynamic test bench is also studied.