• The Journal of the Korea institute of electronic communication sciences
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• v.12 no.4
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• pp.545-548
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• 2017

This study describes the design and implementation of IFA(Input Filter Assembly) for Digital Satellite Communication. The IFA unit for SHF band consists of coupler, LPF(Low Pass Filter) and input Filter. Through the pre-simulation analysis of space environment, the possibility of the malfunction of equipment minimized and we designed a reliable IFA through simulation for vibration analysis generated during the launch, and compared pre-simulation of main performance results to test results about main performances of IFA after production.

• CDE review
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• v.14 no.1
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• pp.32-37
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• 2008

• 발명특허
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• v.33 no.3 s.380
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• pp.38-40
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• 2008

• Proceedings of the KAIS Fall Conference
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• 2000.04a
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• pp.14-14
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• 2000

• Proceedings of the Materials Research Society of Korea Conference
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• 2011.05a
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• pp.4.2-4.2
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• 2011

본 발표에서는 고분자나 탄소나노튜브, 그래핀 등 탄소소재의 분자배열을 다양한 형태로 조절할 수있는 분자조립공정을 통해 비교적 저비용으로 대면적에서 나노구조체를 제작할 수 있는 다양한 기술들을 소개할 것이다. 특히 블록공중합체의 분자조립현상을 기존에 반도체나 디스플레이에 쓰이고 있는 ArF 리소그라피나 I-line 리소그라피와 융합하여 대면적에서 분자조립 나노패턴을 제작할 수 있는 기술들을 소개할 것이다. 또한 탄소나노튜브와 그래핀등 탄소소재를 용액공정이나 촉매나노패턴공정을 통해 3차원적인 다양한 형태로 조직화하는 신기술들도 소개할 것이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.536-542
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• 2017

A great deal of difficulty is encountered in the thermo-mechanical analyses of nozzle assembly for solid propellant rocket motors. The main issue in this paper is the modeling of the boundary conditions and the connections between the various components-gaps, relative movements of the components, contacts, friction, etc. This paper evaluated the complex phenomena of nozzle assembly during burning time with co-simulation which include fluid, thermal surface reaction/ablation and structural analysis. The validity of this approach was verified by comparison of analysis results with measured strains.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.4
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• pp.36-43
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• 2018

A great deal of difficulty is encountered in the thermo-mechanical analyses of nozzle assemblies for solid propellant rocket motors. The main issue in this paper is the modeling of the boundary conditions and the connections between the various components-gaps, relative movements of the components, contacts, friction, etc. This paper evaluates the complex phenomena of nozzle assemblies during burning time with co-simulations that include fluid, thermal surface reaction/ablation, and structural analysis. The validity of this approach is verified via comparison of analysis results with measured strains.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.162-165
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• 2004

A layout of regenerative liquid rocket engine using turbo pump has been designed for development of high performance liquid rocket engine. each components of engine system was placed by considering assembly and characteristic. first stage engine system is controled by one plane of axis gimballing and composed of four engine assembly to cluster with launch vehicle. second stage engine system is controled by two plane of axis gimballing and composed of one engine assembly. assembly and disassembly processes and required program have been developed. various shape of instruments were also developed for carrying out assembly and disassembly process efficiently

• Transactions of the Korean Society of Mechanical Engineers A
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• v.30 no.11 s.254
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• pp.1433-1438
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• 2006

A systematic approach to socket shape design of a concave piston assembly for a high pressure hydraulic pump of an excavator is presented in this paper. A design model is given and a methodology of socket shape design is proposed. An axisymmetric rigid-plastic finite element method is employed for predicting the approximate socket shape formed by a rotary forming process as well as for simulating the test process for separating the shoe from the piston assembly designed. It is verified that the predictions are in good agreement with the experiments. The approach is successfully applied to developing an optimal concave piston assembly.

• Journal of the Korea Institute of Military Science and Technology
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• v.4 no.1
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• pp.137-146
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• 2001

According to the advanced development of Light Weight Torpedo, the overall items related with the parachute type and gore layout and air stabilizer of the parachute for fixed and rotary wing aircraft are described in this paper. Also, the drag-area which should satisfy the firing envelope, parachute inflation characteristics, stability of parachute and torpedo in airdropping, water entry impact on torpedo and parachute constituted the principle design factors. The important trial and errors occurred in the step of performance of the parachute for fixed and rotary wing aircraft are investigated and analyzed.