• Transactions of the Korean Society of Mechanical Engineers A
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• v.31 no.2 s.257
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• pp.260-268
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• 2007

Demand for the use of 3D CAD DMU systems over the Internet environment has been increased. However, transmission of commercial 3D kernels has delayed the communication effectiveness due to the kernel size. Light weight CAD geometric kernel design methodology is required for rapid transmission in the distributed environment. In this paper, an assembly data structure suitable for the top-down and bottom-up assembly models has been constructed. Part features are stored without a hierarchy so that they are created and saved in no particular order. In particular, this paper proposes a new assembly representation model, called multi-level assembly representation (MAR), for the PDM based assembly DMU system. Since the geometric kernel retains assembly hierarchy and topological information, it is applied to the web-viewer for the PDM based DMU system. Effectiveness of the proposed geometric kernel is confirmed through various case studies.

• Journal of the Korea Institute of Military Science and Technology
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• v.19 no.1
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• pp.1-8
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• 2016

In this paper, we have described the performance improvement of surveillance radar to prevent damage or malfunction of surveillance radar RF head unit due to the strong reflections caused by artificial obstacles at close range. We have proposed a technique to improve the performance of the RF head unit as a solution to overcome the limitations of the operating system and improve radar performance. We have verified the effectiveness of the improvement by comparing the before and after results applied to actual system.

• Journal of the Korean Society for Precision Engineering
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• v.26 no.9
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• pp.31-37
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• 2009

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.117-125
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• 2004

This paper describes the test technique for the full-scale airframe durability test according to the military handbook(MIL-HDBK-1530) and ASIP(Aircraft Structure Integrity Program) to evaluate structural integrity and to obtain basic data for IPA(Initial Production Approval) of the Korean advanced trainer(T-50). This paper covers the full-scale airframe floating setup technique, the optimized test load simulation method, test rig design technique, test setup design and installation techniques, test safety device design and operation technique, and durability test results. As 1st life durability test was successfully performed, it was confirmed that this method is available in a full-scale airframe structural test.

• Journal of the Korean Applied Science and Technology
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• v.37 no.6
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• pp.1597-1604
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• 2020

In this study, a synthesized poly(amino acid) self-assembly grafted with valine molecules was investigated on the skin activity of skin growth factors. The amphiphilic grafted poly(amino acid) derivatives were successfully synthesized by varying of degree of substitution(DS) and polymerization (DP) with valine molecules forming a β-sheet structure. Then, the pro-collagen biosynthesis of EGF(epidermal growth factor) was improved by 20%, and the inhibitory ability of tyrosinase activity was increased by 6.5 times by self-assembling of EGF with the poly(amino acid)s having β-sheet structures. This strategy of preparing protein self-assembly with poly(amino acid) derivatives will help improve the stability of protein growth factors and use it in medicals as well as cosmeceuticals through skin improvement.

• Journal of the KSME
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• v.55 no.5
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• pp.30-33
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• 2015

이 글에서는 다양한 분야에 응용될 수 있는 부품 및 조립체 CAD 모델의 단순화를 위한 다양한 방법 및 최근 동향에 대해 소개한다.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.28.1-28.1
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• 2009

고해상도 카메라 혹은 영상레이더 안테나를 장착하여 지구를 관측하는 인공위성의 구조체는 발사하중 및 우주환경의 궤도 상에서 탑재된 장비를 보호하게끔 설계되고 제작된다. 구조체는 발사체와의 공진을 피할 수 있는 강성을 가져야 하며, 주 구조물의 강도는 발사체로부터의 하중을 견딜 수 있도록 설계된다. 또한, 극한 우주환경 하에서 구조체의 변형이 최소화 되도록 설계된다. 상기 설계 내용이 완벽하게 구조체에 반영되기 위해서는 우주용자재 및 공정의 적절한 선정이 이루어 져야 한다. 이 논문은 인공위성 구조체에 사용된 Metal, Non-metal 및 조립용 Hardware 자재 (규격 포함)와 측면패널/플랫폼 및 태양전지판 Substrate 등 주요 구조물의 제작공정에 대하여 기술한다. 그리고, 국산화가 이루어진 조립용 Hardware의 Dry Film Lubricant 공정에 대해서도 기술한다.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.40-44
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• 2007

Based on the optical design type, the large aperture payload has not only a different characteristic of design, assembly and alignment but also its own merits and demerits. The analysis of characteristic has been performed according to the optical design type and based on this result, our camera is 4 reflective mirror system based on the Korsch type. Each mirror assembly is to be verified in the mirror manufacturer and the Optical Module(OM) will be assembled, aligned and tested by KARI. The final performance of camera depends on the several factors, especially, the optical performance of its OM In parallel with the optical design the conceptual design of OM assembly and alignment has been performed. In this paper, the analysis of characteristic has been performed according to the optical design type and the conceptual design of OM assembly and alignment was described with regard to optical performance.

• Journal of Aerospace System Engineering
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• v.15 no.1
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• pp.72-79
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• 2021

In this study, as part of the development of an autonomous flying personal aircraft, an equivalent model of the main wing assembly of an Optionally Piloted Personal Air Vehicle (OPPAV) was developed. Reliability of the developed equivalent model was verified by eigenvalue analysis. The main wing assembly consisted of a main wing, an inboard pod, and an outboard pod. First, for developing an equivalent model of each component, components to produce the equivalent model were divided into several sections. Nodes were then created on the axis of the equivalent model at both ends of each section. In addition, static analysis with unit force and unit moment was performed to calculate the deformation or the amount of rotation at the node to be used in the equivalent model. Equivalent axial, bending, and torsional stiffness of each section were calculated by applying the beam theory. Once the equivalent stiffness of each section was calculated, information of a mass and moment of inertia for each section was entered by creating a lumped mass in the center of each section. An equivalent model was developed using beam element. Finally, the reliability of the developed equivalent model was verified by comparison with results of mode analysis of the fine model.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.98-103
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• 2004

This paper describes a system design of Launch Ground Complex for the Korea Space Launch Vehicle-I which will play so important roles of successful execution for Korea National Space Development Program. Launch Ground Complex has to supply safe work space, construction and equipments for assembling, check-out and launching of the space launch vehicle, and it consists of Mechanical, Electrical, Fluid Ground Support Equipment and Infrastructure. Mechanical Ground Support Equipment consists of Launch Pad, Mobile Assembly Tower, Umbilical Tower, Lightning Tower, Theodolite Building and Auxiliary.