• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.5
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• pp.1-6
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• 2009

A development of a composite solid propellant is carried out for an application to gas generators as an energy source of rocket system. With HTPB as a propellant binder which has 80% of particle loading ratio, a favorable rheology, and moderate curing properties at the range of $-50^{\circ}{\sim}70^{\circ}C$, AN is selected as the first kind of oxidizer having the characteristics of a low flame temperature, minimal particle residual as well as nontoxic products. AP is the second oxidant for ballistic property control. A series of experiments for the improvement of physical properties were conducted and resulted in the propellant formulation having 30% of strain rate at 8 bar of max. stress.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.159-162
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• 2009

Using the numerical code for the interior ballistics, the performance of the interior ballistics with the characteristic of the configuration of the solid propellant has been investigated. In existing research, only ball type solid propellant is considered but at this research, cylinder and single slot type solid propellants are considered. Definite the change of performance of the interior ballistics according to specific surface area.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.4
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• pp.24-32
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• 2008

We made a new propellant formulation to improve the productivity of Base Bleed Unit(aka BBU) by reducing of the curing time. We made an experiment with new propellant formulation such as binder characteristics and manufacturing process. In addition, we already tested several basic characteristics and the final performance of the new propellant. According to the test report, it was not only satisfied with all requirements in the specification, but it also contributed to improve productivity and reduced 53% of the curing time.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.133-144
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• 2005

Enhancements to propellants provide an opportunity to either increase performance of an existing launch vehicle. One of the promising technologies is the use of densified cryogenic propellants such as liquid hydrogen and liquid oxygen. The main advantage of densified cryogenic propellants is the increase in propellant mass fraction. Increased propellant mass fraction means increased payload mass to orbit. This paper reviews the basic principles and current technology trends for cryogenic propellant densification technologies. Several promising densification methods are presented focused on liquid oxygen densification. Engine and vehicle performance analyses are also presented to quantify the potential performance benefits of densified propellants in an overall system. And suggestions of application scheme for satellite launch vehicle is made.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.47-50
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• 2003

JA2 Propellants, made by non-solvent process, are of great interest for the tank gun propellant. This is due to high energy. The grain geometries of JA2 and modified JA2 propellant were designed for application to 105mm APFSDS projectile. The combustion, thermochemical, and interior ballistic properties of the propellant were tested and calculated. The performances of the propellant were evaluated out using 105mm slug T2 projectiles and 105mm tank gun. The muzzle velocity of the propellants was higher than that of the KM30 for K274 projectile.

• Current Industrial and Technological Trends in Aerospace
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• v.9 no.1
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• pp.130-138
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• 2011

A vent relief valve performs as a safety valve, which ensures ventilation of propellant tank during filling and protection from tank overpressure after filling. Because of the reliability and cost saving, the virtually same vent relief valve has been used on all US cryogenic liquid fueled launch vehicles. Some modification to the valve has been applied to satisfy the various mission requirements of launch vehicles. This paper reviews the main technology trends of the vent relief valve applied to the propellant feed system for launch vehicle with respect to design and manufacture. This paper also introduces the operating technology of vent relief valve applied for launch vehicles of advanced countries in space development.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1176-1179
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• 2017

In this study, internal ballistic analysis theories of dual-thrust solid rocket motor using two kinds of propellant are found, and the theories are applied to develop internal ballistic analysis model. Internal ballistic analysis which is dual-thrust solid rocket motor using two kinds of propellant is carried out an applying of the random figures of two kinds of propellant and an analyze of the test results. Through this analytical model was able to an applying internal ballistic analysis for dual-thrust solid rocket motor using two kinds of propellant.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.2
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• pp.62-69
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• 2005

The design method to calculate the main features of propellant tank pressurization system during the development procedure of propellant feed system of the liquid rocket engine was suggested. We have considered the influences of parameters of pressurization gas on the efficiency of the thermodynamic processes in the tank. The optimum value of temperature and velocity of pressurization gas at the entrance of tank are obtained by the suggested way.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.6
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• pp.1-8
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• 2007

The objective of the present work is to characterize design parameters of solid propellant ignitor for composite, double base, and nitramine propellants using arc image furnace. Arc image furnace and fiber optics surface reflectometer were used to measure ignition delay time and reflected optical energy of several compositions of composite, double base and nitramine base rocket propellant at different pressure levels each other. The order of ignitability was double base > composite> nitramine propellants at initial pressure of over 75 psia. The highest ignition energy was needed to ignite nitramine propellant, however, the ignition delay time decreased abruptly as the pressure increased up to the range of $75{\sim}400$ psia. The absorbtion of radiation energy could be increased by the addition of small amount of opacifiers as carbon black, ZrC, WC and burning catalyst.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.4
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• pp.50-58
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• 2016

Korean Space Launch Vehicle (KSLV-II) Propellant Supply System charges liquid oxygen and kerosene to each propellant tank for the stages. To charge the launch vehicle propellant tank safety, the propellant charge flow rates and scenarios should be defined. First, the Propellant Supply System was modeled with 1D flow analysis program. The control valve capacity and orifice size were calculated by performing the 1D steady state simulation. Second, the 1D transient simulation was performed by using the steady state simulation results. As propellants were being charged at the each tank, the increased tank liquid level decreases the charge flow rate. Consequently, the proposed supply system satisfies the required design charging conditions.