• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.466-475
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• 2011

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.616-623
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• 2012

Turbopump is a key component in liquid rocket engines, and reducing weight while maintaining structural safety is one of the major concerns of turbopump designers. To reduce the weight aluminium alloy castings instead of steel casings are introduced. The casting process is especially useful for enhancement of productivity and for reduction of product costs. But, since castings are used in space vehicle engines, reliability cannot be compromised therefore proper design, production process and thorough investigation should be performed to ensure structural integrity. In this study inlet casings for a fuel pump are casted with A356.0-T6 alloy and using one of them a burst test is conducted to ensure structural integrity. Structural analysis is performed for simulation, and with multiple strain gages strains are measured and compared with predictions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.236-241
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• 2011

The position effect of the solid propellant in the combustion chamber on the decrease of the differential pressure has been investigated using the IBcode. Generally the metallic cartridge or CCC (combustible cartridge case) as the propellant for the cannon has been loaded. The position of the propellant(cartridge) is, therefore, a major factor for the interior ballistics in case the combustion chamber is larger than the cartridge. In this study, three cases of the existence of empty space in the chamber has been considered. As results, the case of the propellant located in the region near the base and breech has shown that the negative differential pressure and the difference between the breech pressure and the base pressure are much higher than those of the case of the propellant located in the center of the chamber. The case of the propellant in the center of the chamber is, therefore, more profitable to improve the performance of the interior ballistics.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.70-79
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• 2011

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.47-57
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• 2011

All solid rocket propellants are divided in two basic classes according to chemical state: homogeneous(double base) and heterogeneous (composite). Today, composite propellants are extensively used as power sources covering the range from gas generators and small rocket systems to large launch vehicles in space programs. The development of composite rocket propellants in the past was mainly directed to thermoset polymers. But, the thermoset composite propellants have the complication in formulation and fabricating process to adapt to rocket system requirements. In contrast to the thermoset propellant, the PVC plastisols composite propellants have the advantages in the view of loss in manufacturing process, low cost of raw material, and stability of the handling process even though moderate ballistic and mechanical properties. It is predicted that the application field of this class will be used more widely than any other classes.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.4
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• pp.80-86
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• 2012

This study is for figuring out a possibility of realization of the thermal protection system(TPS) for temporary use under high temperature condition and improving a design of the future TPS. On this purpose, environmental condition of the system has been simplified: the boundary conditions consist of a internally heating surface and a externally heated surface which is simulating the external high temperature condition. Configuration of the system is simplified as a hexahedon. Melting characteristics of the phase change material(PCM) and air temperature variation of TPS with or without connector have been numerically analyzed and compared. As a result of numerical analysis, the heat from the internally heated surface could not be effectively transferred. Therefore, temperature of inner space has been increased.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.2
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• pp.128-134
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• 2013

A 2-way solenoid valve regulates to maintain the pressure of ullage volume of propellant tanks when the command is given by control system for the liquid-propellant feeding system of space launch vehicle. The simulation model of solenoid valve for pressurization is designed with AMESim to verify the designs and evaluate the dynamic characteristics and pneumatic behaviors of valve. To improve the accuracy of the model, numerical flow analysis by using FLUNET code. The simulation results of their operating durations of valve by AMESim analysis are matched up with the results of experiments and validate valve model. Using the model, we analyze performance of valve; opening/closing pressure, operating time on various design factors of basic valve and control valve; geometrical size of valve seat, ratio of basic valve and sealing area.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.2
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• pp.125-130
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• 2018

The technology development of a high performance upper stage engine for a GEO(GEostationary Orbit) KSLV(Korea Space Launch Vehicle) is undergoing in Korea Aerospace Research Institute. KSLV is composed of an open cycle engine with gas generator, which is for a low orbit launch vehicle. However the future GEO launch vehicle requires a high performance upper stage engine with a high specific impulse. The staged combustion cycle engine is necessary for this mission. In this paper, current progress and future plan for staged combustion cycle engine development is described.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.2
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• pp.29-37
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• 2018

This paper reports the preliminary firing test performed with an ADN-based monopropellant using a 5 N scale thruster. ADN-based propellant and catalyst was fabricated and catalytic combustion of propellant was characterized by DSC-TG analysis. Although an explosion in the catalyst bed was occurred, high temperature in the catalyst bed obtained and demonstrated catalytic combustion of the propellant. Preliminary test results motivates the research for catalysts with better thermal stability.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.1
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• pp.16-27
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• 2018

A basic numerical analysis was performed to confirm the possibility of combining a dual bell nozzle and an Expansion-Deflection(E-D) nozzle. The dual bell nozzle was designed based on the first-stage nozzle of the Korean Space Launch Vehicle that is being developed, and the E-D nozzle concept was applied to the dual bell nozzle. The inlet condition was analyzed by applying eight types of frozen flow analysis, and k-${\omega}$ SST was selected as the turbulence model. The number of optimal grids was obtained as 240,000 through the grid sensitivity analysis. As a result, it was confirmed that the transition altitude increased owing to over-expansion when the E-D nozzle concept was applied to the dual bell nozzle, and the specific impulse gain was obtained at high altitudes compared with the KSLV-II first-stage engine.