• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.4
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• pp.423-430
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• 2010

Hot closed-forging process and the die used for forming an automotive flange were analyzed from the viewpoints of heat transfer, grain-flow lines, and stresses to obtain a forged product without defects such as surface cracks, laps, cold shots, and partial filling. The forging process including up-set, pre-forging, final forging and pressing forces was investigated using finite element analysis. The influence of the preform die and the ratio of the heights of the upper die to lower die on the forging process and die were investigated and a die shape ($10^{\circ}$ for the preform die, and 1.5:1 ratio for the final die) suitable to achieve successful forging was determined on the basis of a parametric study. All parametric design requirements such as strength, full filling, and a load limit of 13,000 KN were satisfied for this newly developed flange die. New dies and flanges were fabricated and investigated. Defects such as partial filling and surface cracks were not observed.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.3
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• pp.47-53
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• 2015

Design parameters required for Methane/oxygen bipropellant small-rocket-engine were derived through a theoretical performance analysis. The theoretical performance of the rocket engine was analyzed by using CEA and optimal propellant mixture ratio, characteristic length, and optimal expansion ratio were calculated by assuming chemical equilibrium. A coaxial-type swirl injector was chosen because of its outstanding atomization performance and high combustion efficiency compared to other types of injector and also a bell nozzle with 80% of its full length was designed. The rocket engine configuration with 1.72 MPa of chamber pressure, 0.18 kg/s in total propellant mass flow, and O/F ratio of 2.7 was proposed as a ground-firing test model.

• Proceedings of the Korea Concrete Institute Conference
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• 2008.04a
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• pp.321-324
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• 2008

This paper presents the results of the performance of compression-type anchor for CFRP tendon. As the results of previous tests, the principal variables for enhancing performance of anchor were sleeve dimensions, inserts, compression pressure, etc. A total of 18 specimens were tested for the performance of compression-type anchor with various inner shapes. Test results revealed that the length of sleeve increased along with the performance of anchor up to 18-22%. Also, the performance of anchor was susceptible to the length of sleeve compared to the surface treatment with the oxide.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.26-31
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• 2005

An efficient estimation of the aerodynamic characteristics for missile configurations is essential in the preliminary stage of a missile design. In this study, a Missile DATCOM family code based on the semi-empirical method was utilized for this purpose. In order to check the accuracy and reliability of the code several test cases have been considered: subsonic flow with high angles of attack and supersonic flow with moderate angles of attack. It turned out that the code in general provides prediction in qualitative agreement with the experimental data and results by other works. Finally, the code was applied to a more complicated missile configuration with canard and freely spinning tail fin.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.70-80
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• 2019

Combustion tests using six bi-swirl coaxial injectors with different shapes and recess lengths were performed in a model combustion chamber capable of flame visualization. By utilizing gaseous methane and gaseous oxygen instead of actual propellants, the effects of injector design and experimental conditions on the flame structure and combustion stability were analyzed. It was found that not only the experimental conditions but also the injector geometry such as the recess length and orifice diameter had a considerable influence on the combustion stability. In addition, it was confirmed that the heat release pattern changed with the occurrence of combustion instability.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.5
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• pp.474-480
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• 2011

Space Imaging Sensor operated on LEO is affected from the Earth IR and Albedo as well as the Sun Radiation. The Imaging Sensor exposed to extreme environment needs thermal control subsystem to be maintained in operating/non-operating allowable temperature. Generally, units are periodically dissipated on spacecraft panel, which is designed as radiator. Because thermal design of the imaging sensor inside a spacecraft is isolated, heat pipes connected to radiators on the panel efficiently transfer dissipation of the units. First of all, preliminary thermal design of radiating area and heater power is performed through steady energy balance equation. Based on preliminary thermal design, on-orbit thermal analysis is calculated by SINDA, so calculation for thermal design could be easy and rapid. Radiators are designed to rib-type in order to maintain radiating performance and reduce mass. After on-orbit thermal analysis, thermal requirements for Space Imaging Sensor are verified.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.1
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• pp.1-8
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• 2020

In this study, a configuration design of a CH₄/LOx small rocket engine was made and test system was established for the performance evaluation. A coaxial swirl injector was chosen because of its remarkable atomization performance and low combustion instability. Three aspect ratios for the combustion chamber configuration, i.e., 1.5, 1.8, and 2.1 were also set for the comparison of the combustion efficiency. The reliability of the thrust measurement rig was enhanced by pre-and post-calibration process. From the preliminary ground hot-firing test, the measured thrust and specific impulse values were 89.2 N and 181.8 s, respectively, which were 21.6% lower than the ideal values. In addition, the efficiency of characteristic velocity was measured as 84.2%.

• Proceedings of the Korean Society for Technology of Plasticity Conference
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• 2004.05a
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• pp.91-94
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• 2004

Preform design techniques have been investigated in efforts to reduce die wear and forming load and to improve material flow, filing ratio, etc. In hot forging processes, a thin deformed part of a workpiece, known as a flash, is formed in the narrow gap between the upper and lower tools. Although designers make tools that generate a flash intentionally in order to improve flow properties, excessive flash increases die wear and forming load. Therefore, it is necessary to make a preform shape that can reduce the excessive flash without changing flow properties. In this paper, a new preform design technique is proposed to reduce the excessive flash in a metal forging process. After a finite element simulation of the process is carried out with an initial billet, the flow of material in the flash region is traced from the final shape to the initial billet. The region belonging to the flash is then easily found in the initial billet. The finite element simulation is then carried out again with the modified billet from which the selected region has been removed. In several iterations of this technique, the optimal preform shape that minimizes the amount of flash without changing the forgeability can be obtained.

• Proceedings of the Korean Society for Technology of Plasticity Conference
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• 2001.10a
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• pp.224-227
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• 2001

The preform design in metal forging plays a key role in improving product quality, such as ensuring defect-free property and proper metal flow. In industry, preforms are generally designed by the iterative trial-and-error approach, but this approach leads not only to significant tool cost but also to the down-time of the production equipment. It is thus necessary to reduce the time and the man-power through an effective method of perform design. In this paper, the equi-potential lines designed in the electric field are introduced to find the preform shape. The equi-potential lines obtained by the arrangement of the initial and final shapes are utilized for the design of the preform, and then applied for obtaining a fine preform in the foging process of the ball-joint socket.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05a
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• pp.526-531
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• 1998

본 논문은 농축도 0.9%의 순환우라늄 핵연료(CANFLEX-RU)에 대한 축방향 출력분포(AFD) 및 반경방향 출력분포(RFD) 특성을 조사하고 CANFLEX-RU 다발이 장전된 CANDU줄 채널의 예비 열수력 해석을 수행하였다. CANFLEX-RU 다발의 4 bundle shift 핵연료 교체 방법에 따라 AFD 분포 특성은 정점(Peak) 열속이 채널 상류쪽으로 이동하였고 채널 중심 부근에서 평탄하거나 다소 오목한 형상을 보여주었다. RFD 분포를 표현하는 적절한 변수로서 국부 다발열유속비를 정의하고, 이 비와 국부 표면열유속비의 상호 관계식을 도출하였다. 연소도에 따른 최외환봉의 국부 다발열유속비 변화를 조사한 결과로서, CANFLEX-RU 다발의 최대 국부 다발열유속비는 초기 연소도에서 발생되었고 이 값 CANFLEX-NU 다발 보다는 크고 37-핵연료봉다발 보다는 작았다. CCP 계산시에 RFD 분포 효과를 고려하는 방안으로서 최외환봉 열유속을 다발의 국부 열유속으로 가정하였다 이는 임계열유속이 -10.2% 감소한 조건을 사용하여 CCP를 계산하는 결과가 되었다. 다발-블균형 계수를 이용한 CCP 민감도 결과와 본 계산에서 얻은 CCP 결과에 의하면, CANFLEX-RU의 CCP 는 CANFLEX-NU에 비교해서 土1.0% 이내로 근사한 분포가 예상되었으며 이는 AFD 분포 효과가 RFD 분포에 의한 CCP 감소를 보상하기 때문이다. 결론적으로, CANFLEX-RU는 열수력적 설계 관점에서 CANFLEX-NU에 비교해서 열적 성능이 저하되지 않았고 따라서 기존 37-핵연료봉다발에 대한 CANFLEX-NU의 열여유도 증가와 같은 장점을 유지할 것으로 예상되었다.