• Proceedings of the Korean Society For Composite Materials Conference
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• 2005.11a
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• pp.215-218
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• 2005

In this research, design scheme of fiber Bragg grating(FBG) sensor system for aircraft application is suggested from the results and the know-how from the fon11er researches on structural health monitoring techniques using fiber optic sensors. Design factors to be taken into consideration were derived for both sensor parts including connection and system parts. For the stability of FBG sensor system, design requirements of temperature, vibration, humidity, electromagnetic interference were presented from U. S. military standards. The direction of software programming which increases stability and perfon11ance of the aircraft with the FBG sensor system was also examined.

• Journal of Ocean Engineering and Technology
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• v.11 no.3
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• pp.69-75
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• 1997

A A12024-T3 plate has been reinforced with AFRP to be a Hybrid-Composite, APAL. The fatigue life of the APAL has been investigated. The effects of bonding surface, numbers of AFRP bonded and AFRP orientation on fatigue life have been compared with A12024-T3 plate. Fatigue life of APAL has been remarkedly increased compared with that of A12024-T3 plate. The fatigue life has depended on bonding surface and AFRP orientation, but no relationship could be found with numbers of AFRP laminates.

• Journal of the Korean Society for Nondestructive Testing
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• v.23 no.5
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• pp.445-454
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• 2003

Health monitoring is a major concern not only in the design and manufacturing but also in service stages for composite laminated structures. Excessive loads or low velocity impact can cause matrix cracks and delaminations that may severely degrade the load carrying capability of the composite laminated structures. To develop the health monitoring techniques providing on-line diagnostics of smart composite structures can be helpful in keeping the composite structures sound during their service. In this study, we discuss the signal processing techniques and some applications for health monitoring of composite structures using piezoceramic sensors and fiber optic sensors.

• Composites Research
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• v.13 no.2
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• pp.61-71
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• 2000

Today, the use of composite materials become an essential part in the design and manufacturing process of the flight vehicles to reduce the structural weight. Since the structural properties can be varied largely due to the stacking sequence of ply angles, it is very important problem to determine the optimized ply angles under a design objective. Thus, in this study, the analysis of static aeroelastic optimization of a composite wing has been performed. An analytical system to calculate and optimize tile aero-structural equilibrium position has been developed and incorporated with the genetic algorithm. The effects of stacking sequence on the structural deformation and aerodynamic distribution have been studied and calculated with the condition of minimum structural deformation for a swept-back composite wing. For the set of practical stacking angles, the design results to maximize the performance of static aeroelasticity are also presented.

• Korean Journal of Materials Research
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• v.9 no.8
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• pp.763-767
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• 1999

Composite materials have been increasingly used in automotive and aircraft industries, naturally leading to active researches on the materials. Carbon-epoxy composites, one of major composite materials, are investigated to determine their thermal characteristics. Under conditions of thermal fatigues composed of repeated heatings and coolings, variations of elastic constants are studied for the carbon-epoxy composites to reveal the thermal nature of the composites. In general, composite materials are known to have decreasing elastic constants with increasing temperatures. However, in contrary to this commonly observed behavior, the results obtained in this investigation for the elastic constants of the carbon-epoxy composites show unexpected phenomena in that the elastic constants initially increase with increasing temperatures to certain point and decrease later with further increase in temperatures when the carbon-epoxy composites are subjected to thermal fatigues.

• Composites Research
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• v.16 no.6
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• pp.41-47
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• 2003

Composites are widely used for aircraft, satellite and other structures due to its good mechanical and thermal characteristics such as low coefficient of thermal expansion(CTE), heat-resistance, high specific stiffness and specific strength. In order to use composites under condition of high temperature, however, material properties of composites at high temperatures must be measured and verified. In this paper, material properties of T700/Epoxy were measured through tension tests of composite specimens with an embedded FBG sensor in the thermal chamber at the temperatures of RT, $100^{\circ}$, $200^{\circ}$, $300^{\circ}$, $300^{\circ}$. Through the pre-test of an embedded optical fiber, we confirmed the embedding effects of an optical fiber on material properties of the composites. Two kinds of specimens of which stacking sequences are [0/｛0｝/0]$_{T}$. and [$90_2$/｛0｝/$90_2$]. were fabricated. From the experimental results, material property changes of composites were successfully shown according to temperatures and we confirmed that fiber Bragg grating sensor is very appropriate to strain measurement of composites under high temperature.

• Proceedings of the Materials Research Society of Korea Conference
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• 2009.11a
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• pp.17.1-17.1
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• 2009

발포금속은 1948년에 Sosnik에 의해 알루미늄에 수은을 증발시키는 방법으로 발포 알루미늄을 제조한 이래, 1951년 Elliot에 의해 진보된 방식인 발포 매개체를 용탕에혼입하는 방법으로 발포금속을 제조하기 시작하였다. 현재 이들 선진국가의 생산방법 및 현황은 균질 기공의 조절, 연속주조 방식과 원가절감, 그리고 제조기술의 진보를 통하여 다양한 분야에 적용되고 있다. 그러나 실용화를 위해서는 요구특성을 만족하고 동시에 가격 경쟁력을 가진 제조기술의 보유 및 개발과 독특한 특성을활용한 새로운 적용 분야의 개척이 필요하다고 생각되며, 이를 위해 Harvard, MIT, Aachen, HMI 등 구미 유수 대학과 NASA, 미국방성등의 연구기관, ERG, 신강(新鋼) wire등 산업체를 중심으로제조 및 특성평가에 관한 기초연구와 활용방안이 활발히 모색중에 있다. 그리고 일부 자동차 생산 업체를중심으로 발포금속을 적용한 초경량, 에너지 절감형의 자동차 부품 소재,항공기 방열판 등에 대한 연구가 활발하게 진행되고 있다. 특히 금속 기체의 GASAR 공법은 Lotus 공법으로 Osaka 대학에서 개발되어 열교환기, 항공기, 방열기 등으로 응용이 확대되고 있다 국내에서 완제품생산은 실내장식용 복합패널로서 한소 프라임이 운영상의 문제로 생산을 중단하였으며, 유닉슨(주), 금강(주)에서 Batch식, 금성산업에서 Pot식이 일부 생산 및 연구가 진행되었으나 현재는 본연구실의 협조로 (주) 폼텍에서 발포패널을 주로 생산하고 있고 (주)드림메탈과 (주)아크로폼텍에서일부 생산되고, (주)동일알루미늄에서는 폐 scrap을 이용한 발포 Al 제조가 연구단계에 있다. 생기원에서는 분말 가열 흡음패널이 개발되었으나 강도와 내열성이 낮아 이들 특성을 향상시크는 연구가 진행중이다. 이들 제품은 성능상으로는 동양강판의 흡음패널과 KIMM의 필터용은연구개발이 낮은 수준이며, 본 연구팀과 공동 개발한 (주)폼텍의 복합패널은 10여 가지의 실용특허로 건축마감재로서 오히려 선진국수준을능가한 상태이다, 한편, 발포금속 기능성 개발은, 이들이 가지고 있는 우수한 특성 때문에 군수용으로부터 민수 산업용까지 전분야에 적용이 가능한 소재이므로 수요처를확장하고 있으므로 제품의 균질성, 안정성과 기능성 개발 향상을 위해 지속적이고 체계적인 연구가 필요하다고 생각된다.

• Journal of Advanced Navigation Technology
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• v.18 no.4
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• pp.304-311
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• 2014

In this paper, we propose a ultra sound inspection technique for automatic defect detection and classification in aircraft composite materials. Using local maximum values of ultra sound wave, we choose peak values for defect detection. Distance data among peak values are used to construct histogram and to determine surface and back-wall echo from the floor of composite materials. C-scan image is then composed through this method. A threshold value is determined by average and variance of the peak values, and defects are detected by the values. PCA(principal component analysis) and QDA(quadratic discriminant analysis) are carried out to classify the types of defects. In PCA, 512 dimensional data are converted into 30 PCs(Principal Components), which is 99% of total variances. Computational cost and misclassification rate are reduced by limiting the number of PCs. A decision boundary equation is obtained by QDA, and defects are classified by the equation. Experimental result shows that our proposed method is able to detect and classify the defects automatically.

• Journal of Advanced Navigation Technology
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• v.25 no.1
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• pp.17-28
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• 2021

Recently, eVTOL, the next-generation of eco-friendly transportation, has been in the spotlight due to global warming along with traffic jams in large cities of many countries. This study benchmark the external features of Hyundai Motors S-A1, a compound eVTOL combined fixed and tilt rotors among many types of eVTOLs, to create the basic configuration using reverse design techniques. Basic configurations were created using CATIA and aerodynamic analyses were performed using the aircraft design and aerodynamic analysis programs, OpenVSP, XFLR5, and the aircraft wetted area, drag, and lift were calculated after selecting the airfoil, incidence angle, and dihedral and anhedral angles through trade study. Also, required powers were estimated for completing the given mission profile and components weight and the total weight were predicted using the estimation formula and data survey.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.24 no.3
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• pp.15-20
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• 2024

Path planning for unmanned aerial vehicles (UAV) is crucial in avoiding collisions with obstacles in complex environments that include both static and dynamic obstacles. Path planning algorithms like RRT and A^* are effectively handle static obstacle avoidance but have limitations with increasing computational complexity in high-dimensional environments. Reinforcement learning-based algorithms can accommodate complex environments, but like traditional path planning algorithms, they struggle with training complexity and convergence in higher-dimensional environment. In this paper, we proposed a reinforcement learning model utilizing a cell decomposition algorithm. The proposed model reduces the complexity of the environment by decomposing the learning environment in detail, and improves the obstacle avoidance performance by establishing the valid action of the agent. This solves the exploration problem of reinforcement learning and improves the convergence of learning. Simulation results show that the proposed model improves learning speed and efficient path planning compared to reinforcement learning models in general environments.