• Journal of Global Scholars of Marketing Science
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• v.4
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• pp.133-151
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• 1999

소매업이 영속기업 으로서 생존하고 지속적으로 성장하기 위해서는 무엇보다도 경쟁상대와의 사이에서 차별화가 가능한 경쟁 업태전략의 전개가 필요하다. 왜냐하면 소매업의 역사는 소매업의 혁신에 의한 경쟁과 구조의 변화과정이라고 볼 수 있는데 그 과정 속에는 소매업 그 자신이 제공하는 제품 서비스의 특징과 소비자의 구매행동과 의식의 변화가 있었기 때문이다. 연구는 주로 소매업에 있어서의 소비자와 경쟁이라는 2가지 요인을 줌심으로 이론 검토를 행함과 동시에 소비자의 소매업태 선택행동에 관한 질문표 조사연구를 실시함으로서 소매전략의 전개 방향성을 제시하려 하였으며 그 예로서 업태개발 전환을 포함하는 소비자 지향의 새로운 소매전략의 전개와 점포로열티 강화전략을 들고있다.

• Proceedings of the Korea Institutes of Information Security and Cryptology Conference
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• 2003.12a
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• pp.113-117
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• 2003

네트워크에서 보안 기능을 전개하는데 있어 정책 기반 전개 방법이 널리 사용되고 있다. 본 논문에서는 정책 기반 보안 기능 전개에 있어 정책을 설정하고 검증하기 위한 프레임을 제시한다 정책 기반 기능 전개에 있어 중요하고도 어려운 문제는 설정한 정책의 정확성(correctness)과 완전성(completeness)을 검증하는 것이지만 이에 관한 기존의 방법은 주로 경험이나 혹은 감시에 의한 끊임없는 정책 갱신이다. 본 연구에서는 기존의 제안된 여러 보안 모델들을 검토해보고 이 모델들로부터 공통적으로 적용할 수 있는 정책의 정확성과 완전성을 위한 제어 프레임을 설계한다.

• 해운
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• no.1 s.59
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• pp.19-22
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• 2009

사상최고의 호황기와 최악의 침체기를 동시에 경험했던 세계 해운업계는 2009년에 글로벌 금융위기가 어떻게 전개될 것인지에 대해 촉각을 곤두세우고 있다. 지난해 9월 미국 리먼브러더스의 파산으로 야기된 글로벌 금융위기가 전세계로 확산되면서 해운시황이 5개월 사이에 최악의 상황으로 곤두박질했기 때문이다. 긍정적인 전망 보다는 부정적인 전망이 우세한 가운데 포스코경영연구소에서‘글로벌 금융위기 전개방향 및 파급영향’을 분석했다. 다음은 그 내용을 정리한 것이다.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.27 no.4
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• pp.278-285
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• 1991

The authors propose to use the slot system in order to improve of the efficiency for the cambered otter boards. The experiment is divided into 2 parts, one is the efficiency model test, and the other is the visualization model test. The hydrodynamic characteristics of the model otter boards were tested by efficiency model test to measure the shearing, drag force of the models and visualization test using hydrogen bubble method to observe the streak-line and time-line of flow around the models, and milk spout method to observe the separation zone in the wake behind the models. This study tested for 5 models such ad without slot, slot position 0.2C, 0.4C, 0.6C and 0.8C. The results obtained are as follows: \circled1 The maximum C sub(L) of model otter board with slot position 0.6C in attack angle 27$^{\circ}$ was the highest of all models, it's value was 1.59. \circled2 In general, the L/D ratio of the one slot otter boards were 16~28% higher than otter board without slot. \circled3 The slot position 0.6C was better than any other slot position, and it's conformed by visiualization. \circled4 As to the model otter board with slot position 0.6C, flow speed of the back side was faster 1.3 to 1.7 times than in the front side. \circled5 The size of the separated zone in case of the model otter board with 0.6C was smaller than that of any other models.

• 프린팅코리아
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• v.8 no.12
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• pp.44-45
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• 2009

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.4
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• pp.53-59
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• 2003

Strain Energy Hinge(SEH) has been used in Korea Multi-purpose Satellite(KOMPSAT) series to deploy the solar panel due to the good record of reliability. However, when it reached a desired deployment position, a large buckling force is applied to the main body. This may cause structural damage and also affect control of the satellite. Therefore, reliable dynamic analysis for the deployment system is required at a design stage. Moreover, various mission of a satellite has made the size of solar panels got bigger, so elastic effect has to be considered seriously to get more precise analysis results. In this paper, a dynamic analysis method to predict the deployment is verified by KOMPSAT-2 deployment test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.38-45
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• 2003

This research is concerned with the dynamic modeling of the multi-purpose satellite with deployable solar arrays equipped with strain energy hinges(SEH). To this end, we proposed the use of the equivalent torsional spring for the SEH and derived the equations of motion assuming that the satellite and solar arrays are being rigid. We also considered the effect of the support string for the ground experiment model, which has been observed as a critical factor affecting the deployment in the ground experiments. From the numerical simulation results, it is found that solar arrays are deployed in a similar pattern but the hub motions are different because of the support strings. It was concluded that the non-gravity deployment of the solar arrays can be approximately simulated by the ground experimental facility. The effects of the support string are also investigated by varying the length of the string. It was found that the current length of the string is adequate for the ground experiment. Ground experimental results will follow.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.12
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• pp.1007-1012
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• 2017

In this study, we performed the deployment test of shape memory polymer specimens for space antenna design. Poly(cyclootene) was cross-linked by dicumyl peroxide to make a PCO shape memory polymer. A miniature specimen with 120 mm diameter for a deployable antenna was fabricated with the PCO shape memory polymer. To investigate the deployment performance, the folded specimen as a temporary shape was heated by two heaters to the $15^{\circ}C$ higher temperature than the glass transition temperature of shape memory polymer. Firstly, the specimen was installed horizontally and tested. The deploying motion was captured by a digital camera and analyzed by a Tracker program. To reduce the effects of gravity, the specimen was installed vertically and tested again. The deployment performance of a shape memory polymer was investigated by comparing the results of horizontal and vertical installation tests.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.28 no.8
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• pp.603-609
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• 2017

In the deployable solid surface antennas, the effects on the performances of antenna due to the structural errors that occur during the deployment are analyzed. The deployable solid surface antennas employed in a satellite are launched in folded configuration and those are deployed in the space environment, and the effects on the antenna performance are calculated depending on the type of surface errors. When the deviation error occurs in one panel, the degradation of performance appears in the side where the incomplete deployment of panel occurs. By assuming that the panel error distribution is in cosine function, the effect of errors are calculated and analyzed with regard to the types and the magnitude of the error. If the antena panel error is uniform, the gain is reduced and pattern is symmetric. For the panel error of cosine 1 or 3 cycle, the main lobe tilts while the pattern is symmetric and the gain reduces for 2 or 4 cycle error.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.94-101
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• 2019

The dynamic characteristics of the composite reflector panels are numerically and experimentally investigated. A dynamics model of the panel is analytically developed based on a deployment mechanism of the antenna. The deployment is passively activated using elastic energy of a spring with two rotational degrees of freedom. Using the flexible multi-body dynamic analysis ADAMS, dynamic behavior of the panels such as velocities, deformations, as well as reaction forces during the deployment, are investigated in the gravity and zero-gravity cases. The reflector panel is manufactured using carbon fiber reinforced plastics (CFRPs) and its deployment characteristics are experimentally observed using a zero-gravity deployment test. The impact response and vibration problems that occur during deployment of the antenna panel have been identified and reliably deployed using dampers.