• Aerospace Engineering and Technology
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• v.9 no.1
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• pp.116-124
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• 2010

Ground complex composed of Assembly Complex(AC) and Launch Complex(LC) which is located on Oenarodo space center in Kohung is necessary for successful launching of KSLV-I. AC performs accepting of a KSLV-I 1st stage and 2nd stage, stage assembly, the integrated launch vehicle, the checked out, and all kinds of performance test, pre-launch tests and processing. At AC, the mechanical support equipments, that is called the technological equipments, are installed in the Launch Vehicle Assembly Test Building(LVATB). These technological equipments have diverse forms of an interface with mechanical/electric device of the launch vehicle and have to provide a condition and the performance guarantee of an optimum in the launching operation process. In this paper, the requirements specification and manufacturing performance test for the mechanical support equipments which are used in the assembly/disassembly and test of the launch vehicle are introduced.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1995.04a
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• pp.535-543
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• 1995

조립체를 표현하는 가장 간단한 방법은 각 부품의 좌표간의 변환 행렬을 이용하여 위 치와 방향을 정의하는 것이다. 이때 각 부품은 가공단계에서 발생한 형상 오차를 가질 수 있는데 그 형용영역은 설계단게에서 공차로 지정된다. 이러한 형상 오차나 공차를 갖는 부품들이 조립시 가질수 있는 위치와 방향의 허용영역을 구한여 조립성을 판단할 수 있다. 조립성이란 주워진 위치에서 조립이 가능한 가 하는것과 조립경로가 존재하는 가 하는 것 이다. 본 연구에서는 조립성 확인을 위하여 인터벌 수를 세분하는 방법의 인터벌 분석을 이용한다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2012.05a
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• pp.259-262
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• 2012

The most of military systems that developed today are composed with many sub-systems for mission execution. The test of military systems for delivery test of mass product such that part test, PCB test, component test, integration test. This paper discusses improving productivity test method that functional test of PCB has a various function. Improving productivity is minimize testing item by man and minimize kind of tester, so that decrease product cost by production time for test. PCB tester be developed many kind of test method that systems were developed by many different engineers. This paper study testing check point for testing that how to minimize of kind of tester, how to automatic test for all of function that have inputs and outputs.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.5
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• pp.87-92
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• 2019

This study is the analysis of causes of printed circuit board (PCB) in collective protection equipment failure and quality improvement. The equipment is a component of the weapon system currently in operation and serves to defend against enemy chemical and biological attack as well as heating and cooling functions. However, during operation in the military, fans of condensate assembly failed to operate. The cause of the failure is the burning of PCB. It was found that the parts were heated according to the continuous cooling operation under the high temperature environmental conditions. Accordingly, the electronic components exposed to high temperature were deteriorated and destroyed. To solve this problem, PCB apply to heatsink. The performance test of improved PCB has been completed. Futhermore system compatibility, positive pressure maintenance and noise test were performed. This improvement confirmed that no faults have occurred in PCB so far. Therefore, the quality of the equipment has improved.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.12
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• pp.1-6
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• 2018

This study examined the quality improvement of printed circuit boards (PCBs) in relation to the power consumption for radar. The radar examined is currently in production and being used by the military. The PCB converts 28 V DC to 5 V DC but frequently malfunctions. Therefore, cause analysis was carried out. As a result, the power consumed by a certain communication IC was very high, and the heat generated by the high power consumption caused damage to the surrounding parts. Accordingly, it was changed to an improved communication IC that meets all the radar system specifications. System tests were carried out for the changed communication IC to check the impact on the system, and environmental tests were performed, which proved that the performance required by the radar system is satisfactory. As a result of this improvement, there has been no history of failure in this PCB so far. Therefore, the quality of this PCB has been improved.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.4
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• pp.292-299
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• 2017

The KUH-1's Wheel Brake Assembly which is Brake System is an essential component to perform flight mission for pilot. It has function of taxing, differential braking and parking to sustain landing capability. However, the skid and abrasion of tire were occurred in mass-produce operation. Also, if it is occurred on the ground, the flight can not be performed. In this case, the defect is a major cause of the decrease in the operation rate of aircraft. In this paper, the cause of the defect in flight was identified and the failure process was organized. Also, it describes design improvements which was derived from troubleshooting and suggests verification results of flight test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.9
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• pp.714-719
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• 2013

A turboprop aircraft for this study is required to operate at icing condition in order that it performs its given mission. So an air intake system of the turboprop aircraft should be designed and verified not only to provide the maximum possible total pressure at engine inlet at normal flight condition, but also to include an inertial separator which protects Foreign Object Debris (FOD) like ice or snow at icing condition from entering into the engine inlet screen which can cause or lead an catastrophic engine failure like engine flame-out or severe damage. So an air intake assembly incorporating a variable geometry inertial separator has been designed and then CFD/structural analysis for the assembly was performed to see its design results. Then 35% scaled model of the air intake assembly was manufactured and wind tunnel test was done. This paper describes the detailed design results for the aerodynamic design, analysis and wind tunnel testing during the development process of the air intake assembly.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.36 no.2
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• pp.203-210
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• 2012

The main rotor control system is an important structural part of a helicopter that manages the thrust and control force of the helicopter. The main rotor control system consists of a swashplate assembly, scissor assembly, pitch rod assembly, guide, etc. The main rotor control system must endure various loads, such as the thrust and control force, and must meet the optimized fatigue safety life. The rotating swashplate is an important structure influenced by the pitch rod load and rotating scissor load. In this paper, the accuracy of a result about the rotating swashplate part of the main rotor control system is proven through comparison between fatigue test and FEM results. Based on this result, we estimate the lifetime and deduce the fatigue safe lifetime.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.11
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• pp.1697-1703
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• 2010

Hydraulic hoses are used as pipelines for transferring power from hydraulic systems in various machineries such as construction equipments, automobiles, and aircraft. Hydraulic hoses protect the system from vibration or impacts, and they are being used to transfer energy in all segments of the industry. In order to protect the system from various external environmental conditions, hydraulic hose assemblies must be able to withstand a wide range of temperatures and pressures, as well as variations in other factors. In previous studies, an acceleration model for the hydraulic hose assembly was developed by taking into account only one of the acceleration factors (temperature or pressure). Therefore, the objective of this study is to develop a comprehensive acceleration model that takes both temperature and pressure into consideration.

• Journal of the Korean Society for Nondestructive Testing
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• v.23 no.5
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• pp.488-496
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• 2003

To establish nondestructive test method for rocket motor assembly with rubber and aerospace composite materials, practicable quality control acoustic emission test method is presented. Structural analysis for motor assembly is performed by ABAQUS code and analysis output result is confirmed by strain gage and AE data. Various specimens were tested and analyzed using strain gage and acoustic emission data. The hit rate of acoustic emission was closely related with case/rubber debonding. This report also describes practicable acoustic emission nondestructive method for evaluating motor case assembly quality assurance in the industrial field.