• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.776-777
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• 2017

The grain burn-back analysis has been required for the calculation of the solid propellant performance. The conventional grain burn-back analysis uses the level set method, but problems in the moving surface analysis may occur. In this study, the face offsetting method has been used for analyzing the moving surface. As results, the face offsetting method has been proven to be useful method for the grain burn-back analysis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.232-235
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• 2011

A typical unsteady internal ballistic analysis model was developed to take account the erosive burning of a solid rocket motor. The variance of local velocity and pressure along grain surface were analyzed by using the continuity and momentum equation. The coefficients of erosive burning were drew from comparing experiment data with analysis. It was investigated that the grain shapes of propellant affect the erosive burning.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.207-210
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• 2009

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, united state is launching sounding rockets in 20-30 flight per year by the NASA program which offer to carry payload weights of 38-680 kg and altitude of 88-1,500 km. Europe is launching in 4-5 flight per year by the ESA program. Japanese sounding rockets are being applied an Antarctic exploration and flight verification in 1-2 flight per year. The case of korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but our development techniques for space launch vehicle lag behind other industries. Therefore, Launch vehicle development should enable with the support and acquirement of advanced technology.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.5
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• pp.132-139
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• 2013

Liquid-propellant rocket engines are widely used all over the world, thanks to their high performances thrust, in particular high thrust-to-weight ratio. The sucess rate of the launching of the liquid propulsion is similar to the solid one even though it has more complex mechanical system. In general, liquid propulsion is seemed as a mature technology, the requirements of a renewed interest for space exploration has led to the development of a family of new engines, with more design margins, simpler to use and to produce associated with a wide variety of thrust and life requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.245-248
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• 2011

A multi pulse rocket motor(MPRM) has several advantages compared to the single one. The range and the terminal velocity of the guided missile can be remarkably increased by the application of the pulse separation device(PSD) to the solid rocket motor which resulted in appropriate thrust distribution. In this study, the full scale heavy type dual pulse rocket motor with the bulkhead type PSD was designed, manufactured, and fire-tested. The bursting time and pressure of PSD were analyzed by the pressure, thrust and vibration results of static fire tests. As a result, the design requirement was verified that bursting pressure is lower than 30% of 2nd pulse operating pressure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.243-246
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• 2009

The axial local regression rate of solid fuel of hybrid rocket is one of important parameter for a design and performance. Steeping method is simple and measure a corrcet regression rate of axial direction not being relevant to a shape of fuel and physical characteristics. In this study, the problem of other measuring equipment was improved and this linear steeping method is provide higher accuracy than the other.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.2
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• pp.55-65
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• 2021

In this study, the design criteria is presented for Finocyl grain, which is easy to generate neutral thrust when designing solid rocket motors. For this purpose, an automated program using drafting method was developed for burn-back analysis and its accuracy was validated. Using this developed program, burn-back analysis was performed with various configuration parameters of Finocyl grain, and the tendency and sensitivity analysis on burning characteristics were performed. Based on this analysis, the design criteria were presented to generate the neutral burning surface area trace for a Finocyl grain.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.511-514
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• 2009

In this study, the combustion characteristics of hybrid rocket fuel with tapered grain port were studied. The regression rate was increased about 17.5% by using the convergence port shape fuel. On the other hand, in case of divergence port shape fuel, any notable difference of regression rate was not observed when compared with regression rate of the cylindrical port shape fuel. Also, in case of convergence port shape fuel, characteristic velocity efficiency was increased. From these results, one can notice that convergence port shape of hybrid rocket fuel can be effective configuration in terms of improvement of combustion efficiency and performance.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.6
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• pp.91-97
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• 2015

The limit values of mechanical properties(MPs) of HTPB/AP/Al Solid Propellant was reviewed according to the rocket motor development procedures and the in-process values of MPs were analyzed by the tool of Process Capability Index. Based on finding the dependency among MPs, the optimization is proposed for reducing the properties defects and for improving the rocket grain safeties.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.7-10
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• 2009

The development and evaluation of solid propellant were performed for the turbopump pyro starter, which start up the liquid propellant rocket engine for the Space Launch Vehicle (SLV). Requirements for the turbopump pyro starter propellant include the production of low flame temperature, low burning rate and nontoxic gas to protect the mechanical corrosion or air pollution. This study describes the development of the solid propellant composition which is based on PCP binder. DHG (Dihydroxy glyoxime), which has advantages of oxygen balance and ignition, was used as coolant. The mechanical properties and burning rate of the propellants were measured. Finally, static fired test was performed to prove the possibility of development.