• Composites Research
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• v.12 no.1
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• pp.19-27
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• 1999

A design development test for carbon/epoxy composite laminates for an aircraft flight control system is performed. The design development test includes moisture absorbing test, tensile, compressive, bearing and lap shear tests. The moisture absorbing behavior for different fiber orientation angles is investigated and the changes in mechanical characteristics are compared. In the in-plane tensile test, the effect of damages such as scratches and impacts is studied. The bearing test is performed for different fastening types. The resulting design allowable stress and environmental load enhancement factor are used for the structural analysis and certification tests for the flight control system.

• Proceedings of the Korean Institute Of Construction Engineering and Management
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• 2007.11a
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• pp.953-956
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• 2007

"Eco-friendly construction"is an emerging issue in the building industry. Main purpose of the eco-friendly construction is to sustain the health and environment of building residents and to minimize the harmful effect on their environment. Apartment residents have great concern on eco-product, since many cases are reported that Sick Building Syndrome is caused by toxic substance from building materials. Environmental performance is to meet through using the highest grade eco-friendly materials. However, generally eco-friendly materials are more expensive than normal materials. Therefore using eco-friendly materials at public housing project is limited to economical aspect. The purpose of this paper is development of eco-friendly material selection model considered cost efficiency. The selection of Eco-friendly finishing materials and their methods are constructed to consider environmental performance level and cost index compositively. Development of eco-friendly material selection method is economic and reasonable one when public housing is constructed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.193-196
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• 2007

The motor case for the KSLV-I KM is the first satellite launch vehicle ever to be developed by Korea to deliver the 100 kg class satellite into Earth's low orbit. This SLV is made of two stages, and the 2nd stage is made of solid rocket motor. The motor case of the KM is made of all composite materials except for the interface structures. Manufacturing process for the motor case such as insulation, filament winding for the motor case, fabrications for the interface structures will be discussed in this paper.

• 한국신재생에너지학회:학술대회논문집
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• 2007.11a
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• pp.193-196
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• 2007

We developed and tested the high pressure hydrogen gas cylinder(type4) for fuel cell vehicle. The working pressure is 350bar. We conducted material tests, production tests and design qualification tests on the developed cylinders according to modified NGV2-2000(hydrogen). The high pressure hydrogen gas cylinder met all the design qualification requirements of ANSI/CSA NGV2-2000 and acquired NGV2 certification from independent inspection agency.

• Journal of Aerospace System Engineering
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• v.5 no.1
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• pp.17-23
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• 2011

Since the time, cost and lack of regulatory information and guidance, one of the largest regulatory obstacles for an airframe manufacturer of polymer based advanced composite materials in certified aircraft applications, is to generate design allowables that will satisfy Airworthiness Regulations. In the past two decades, the design allowables used in military aircraft had been generated and applied in Korea, however the qualification of composite materials used in certifying airframe structure was not accomplished for design and demonstration of compliance to applicable airworthiness regulation. It is the intend of this paper that provide the basis of composite material qualification for small aircraft certification to the airworthiness regulation.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.43-48
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• 2015

This paper presents the systematic and procedural approaches to ensure the safety of the composite material domestically developed and produced, for its use in the structure of aeronautical product in accordance with the applicable international standard, and to enhance its creditability. Based on this approaches, this paper eventually proposes the practical future plan to encourage and expand the adoption of domestic composite material as part of aeronautical product by aircraft manufacturer in global market.

• Journal of Aerospace System Engineering
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• v.9 no.3
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• pp.8-11
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• 2015

Since the late 1990's, FAA, NASA and the aerospace industry have worked together to develop the sharing system of the composite material qualification databases which were obtained through the standardized fabrication and testing procedures. The result was what is now known as the AGATE(Advanced General Aviation Transport Experiments) or NCAMP(National Center for Advanced Materials Performance) methodology, a more cost-effective concept that shifts the major responsibility for qualification and testing from the aircraft manufacturer to the material supplier. The properties of composite materials are largely dependent on the testing as well as the raw material properties and the manufacturing process including the process control parameters. Thus it is important in the composite material qualification to comply with the standardized testing procedures. In this paper, I will describe the standardized witness methodologies of certification engineers to reduce the effect of testing variability within the qualification data.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.37 no.5
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• pp.619-624
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• 2013

A bendable electronic module is developed. In this module, thin silicon electronic chips are embedded in a polymer-based encapsulating adhesive between flexible copper-clad polyimide layers. During the qualification test of a harshly thermal-hygroscopic complex loading condition, delaminations occur inside the module layers. A finite element model is developed for the module. To investigate the effect of hygroscopic stress on delamination, the results of the thermal and thermal-hygroscopic loads are compared. The analysis results reveal that the hygroscopic effect more strongly affects delamination than does the thermal effect. The potential failure mechanisms of the module are investigated based on the stress analysis.

• Journal of the korean academy of Pediatric Dentistry
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• v.29 no.3
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• pp.423-429
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• 2002

Recently, the clinical uses of flowable composite resins have increased because of fast, convenient and excellent accessibility, but little has been reported about physical properties of flowable resins. The purpose of this study was to measure and compare the physical properties(compressive strength, relative flowability, relative radiopacity) of 4 contemporary flowable composite resins(Filtek flow, Tetric Flow, Revolution Palfique Estelite LV high flow). The results were as follows; 1. There were no significant differences between 4 flowable composite resins in compressive strength, but all were lower than that of traditional hybrid composite resin(p<0.001). 2. The relative flowability were increased in order of Palfique Estelite LV high flow, Revolution, Filtek flow, Tetric Flow and sealant(p<0.001), but there were no significant differences between Filtek flow and Tetric Flow. 3. There were significant differences between flowable composite resins in relative radiopacity and they showed similar or higher radiopacity than dentin(p<0.001), especially Tetric Flow and Filtek Flow showed higher radiopacity than enamel(p<0.001). This results suggested that the stress of application area have to be considered since flowable composite resins have lower compressive strength than hybrid composite, and the differences of flowability between these flowable composite resins can be considered when they are selected. All tested flowable composite resins showed optimal radiopacity to ISO's recommend.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.6
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• pp.26-34
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• 2007

The efforts to develop high performance aircraft engines are successively progressed with development of recent technology. The reliability of individual parts and the safety of engine systems are reduced if high efficiency components, high strength materials, and precise controls are applied to the engine with complexity to increase engine performance. In this paper, the regulation requirements and assessment technique for aircraft engine safety are considered, and the result of safety assessment on a turbine case cooling system of high efficiency turbofan engine is presented.