• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.372-375
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• 2004

The UV radiometer payload was launched successfully from the west coastal area of Korea Peninsula aboard KSR-III on 28, Nov 2002. KSR-III was the Korean third generation sounding rocket and was developed as intermediate step to larger space launch vehicle with liquid propulsion engine system. UV radiometer onboard KSR-III consists of UV and visible band optical phototubes to measure the direct solar attenuation during rocket ascending phase. For UV detection, 4 channel of sensors were installed in electronics payload section and each channel has 255, 290, 310nm center wavelengths, respectively. 450nm channel was used as reference for correction of the rocket attitude during the flight. Transmission characteristics of all channels were calibrated precisely prior to the flight test at the Optical Lab. in KARI (Korea Aerospace Research Institute). During a total of 231s flight time, the onboard data telemetered to the ground station in real time. The ozone column density was calculated by this telemetry raw data. From the calculated column density, the vertical ozone profile over Korea Peninsula was obtained with sensor calibration data. Our results had reasonable agreements compared with various observations such as ground Umkhr measurement at Yonsei site, ozonesonde at Pohang site, and satellite measurements of HALOE and POAM. The sensitivity analysis of retrieval algorithm for parameters was performed and it was provided that significant error sources of the retrieval algorithm.

• Journal of the Korean Institute of Gas
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• v.26 no.2
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• pp.9-13
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• 2022

Electric wheelchairs, the output from the motor is mainly applied to a speed reducer using a power transmission device such as a belt or a chain. However, although a speed reducer using a belt or chain is a simple device, it occupies a lot of space and has a space limitation, so it is not suitable for an electric wheelchair driving part. However, since the speed reducer of the planetary gear type is decelerated on the same axis, the volume can be reduced, so the space constraint is less than that of the belt or chain type reducer. Therefore, in this study, a driving part that can obtain great propulsion with a speed reducer using a planetary gear type was developed through a study on the driving part of a wheelchair that can be switched between manual and electric. Accordingly, the tooth shape of the planetary gear applied to the reducer was designed using the Kisssoft program. In addition, the drive part was designed to be applicable to the existing wheelchair wheels, and the mechanism was optimized for the manual/electric switching principle and operation principle of the drive part. Based on the research contents, the final design and manufacture of the wheelchair reducer drive unit in the form of a planetary gear having one sun gear, two planetary gears and one ring gear was carried out.

• Proceedings of the KIEE Conference
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• 2006.07d
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• pp.1856-1857
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• 2006

The existing automation transfer systems such as AGV(Automated Guided Vehicle) have many problems (maintenance, accuracy, velocity, etc.) and wastes of a vast space and time. Hence we have suggested to LMTT(Linear Motor-based Transfer Technology). This paper deals with fundamental LMTT, and proposes a concept of mass reduction and propulsion control for LMTT when it is starting and reaching an object by using lift-force. By applying optimal controller and the repulsive lift forte in the LMTT, a large percent of vehicle weight is compensated and it reduces friction, then it needs less thrust force to propel the vehicle.

• Journal of Ocean Engineering and Technology
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• v.11 no.4
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• pp.221-226
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• 1997

This study was carried out for the hull form development of G/T 340ton class high speed fishery patrol ship by Chosun University at the Circulating Water Channel cooperatively with Korea Maritime Service. Same size of 15knots class fishery patrol ship was selected as a parent form (Model number : CU-015), and modified fore and after body to be suitable for the operation at 20 knots. To minimize the breaking wave in the vicinity of fore body at high speed zone, high bulb nose and slender fore body hull form was chosen as an initial condition. Meanwhile, to ensure the engine room space keeping high resistance-propulsion performance, U-type stern hull form was developed.

• Journal of the Korean Society of Safety
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• v.10 no.1
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• pp.3-8
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• 1995

The anemometer measurements were obtained from stationary hot-film probe mounted between the forward and rear rotors of a model CRP which rotated the forward and different directions. Data collection was done at several locations between rotors. To establish rotor-rotor interaction flow mechanism that contributes noise increasement of the CRP, methods of simple and the double condition-at sampling have been developed. The former uses to find similarity of the wake the later fixes the forward rotor position in time or space and permits averaging the mean wake at any fixed rotor angular location. The variation of the forward wake Is strongly depending upon the rear rotor location.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.3
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• pp.63-70
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• 2016

The pyrotechnic separation devices are widely used in space systems and guided weapons during the launching and operations, however, they generate intensive pyroshock and fragments that can cause critical damages or the malfunction of electric devices onboard. There have been proposed many types of alternative devices to avoid pyro-induced problems since 1960's. A ball-type separation bolt is the one of alternative Pyrotechnic Mechanical Devices (PMD). In this study, the detail separation behavior of the ball-type separation bolt is analyzed using ANSYS AUTODYN. A simplified one-dimensional mathematical model, consisting of a combustion model and 5-stages of differential equation of motions, is also established to effectively describe the entire separation process.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.3
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• pp.40-47
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• 2014

The grain burn-back analysis has been performed for the internal ballistics analysis code to be used for the optimal design of the space launch vehicles. The grain burn-back has been used to calculate the burning surface that is essential to the internal ballistics. The calculation of internal ballistics code used in the optimal design is repeated until satisfying the required performance through the change of the design parameter. Therefore, the burn-back method applied to the internal ballistics analysis should be easy to change the design parameter and calculation time should be short. In this study, a burn-back analysis code has been developed using the analysis method. Also, geometric parameters of the grain have been selected and organized. The developed code has been verified by comparison of results of a numerical method.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.6
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• pp.113-119
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• 2013

A main oxidizer shut-off valve (MOV) controls the supply of cryogenic liquid oxygen to the combustion chamber of liquid rocket engines by on/off operations. The main subjects to be introduced are not only the valve transient response during valve on/off procedures but also the characteristics of pneumatic and seat/poppet parts as core technologies in the development of the MOV, which is expected to be adopted for the Korea Space Launch Vehicle II. It is shown that the analytical prediction of the transient valve travel is in good agreement with experimental results. Friction and elastic forces on the valve moving part are quantitatively evaluated by structural analysis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.691-698
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• 2017

In this study, the injector transfer function (ITF) of a gas-gas coaxial jet-swirl injector is measured by applying excitation to jet or swirl flow using a loudspeaker. As a result of measuring the ITF according to the variation of feed system length, the ITF peak occurs at the resonance frequency of the space where the perturbed flow passes. When applying the excitation to the jet flow, as the jet flow increases up to 56 slpm, the magnitude of ITF decreases, and ITF increases thereafter. Therefore the larger the velocity difference between the jet and the swirl flow, the larger the ITF. In the case of the swirl excitation, the ITF decreases as the jet flow increases because of the decrease of the energy with respect to the constant flow at the downstream. This difference is caused by the location of the hot wire anemometer on the downstream of the injector center axis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.104-107
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• 2017

The power-pack combustion test of technology demonstration model(TDM0) for 9 tonf-class staged combustion cycle engine development was conducted in the Upper-stage Engine Test Facility(UETF) of Naro Space Center. The power-pack model of TDM0 was composed of a pre-burner, a turbo-pump and propellant supply systems without a main combustor. In the power-pack combustion test, we confirmed the linked working condition and verified the main functional variation of the power-pack for the engine system test.