• Transactions of the Korean Society of Mechanical Engineers
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• v.17 no.11
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• pp.2704-2710
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• 1993

A simple and straightforward method is introduced for developing continuum beam-rod model of a box-beam typed aircraft wing with composite layered skin based on "energy equivalence." The equivalent continuum structral properties are obtained from the direct comparison of the reduced stiffness and mass matrices for box-beam typed wing with those for continuum beam-rod model. The stiffness and mass matrices are all represented in terms of the continuum degrees-of freedom defined in this paper. The finite-element method. The advantage of the present continuum method is to give every continuum structural properties including all possible coupling terms which represent the couplings between different deformations. To evaluate the continuum method developed in this paper, free vibration analyses for both continuum beam-rod and box-beam are conducted. Numerical tests show that the present continuum method gives very reliable structural and dynamic properties compared to the results by the conventional finite-element analysis. analysis.

• Journal of the Korean Society for Nondestructive Testing
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• v.30 no.1
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• pp.54-59
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• 2010

After the advent of B787(Boeing Co.), a civil aircraft using composite materials more than 50% of it total structural weight for weight savings，best performances and efficiencies, various endeavors to develop and apply the state of art of structural health monitoring(SHM) technologies for composite aircraft have been made for many years. Despite their plentiful advantages composite aircraft structures are susceptible to the hidden or barely visible impact damages(BVID) and excessive loads that if unchecked may lead to lower structural integrity, loss of operational performance and finally a sudden catastrophic failure of the aircraft structure. In this paper background of SHM technology and relevant technologies for application of SHM technology to the composite aircraft in the near future and requirements for certification of SHM system are shortly presented.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.22 no.3
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• pp.60-67
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• 2014

Technical history of VTOL aircraft is examined from the early helicopter appearance to recent experimental rotorcraft in order to distinguish the core issues of those aircraft. Performance and technological challenges of some VTOL aircraft such as tilt rotor, convertiplane, gyroplane, and coaxial helicopter are discussed. As a new generation high performance rotorcraft, Sikorsky X2 is intensively investigated. Considering the developmental history of X2, the autorotational ability at high speed is recognized as a core technology. Analytic method of autorotation and some results are shown and presents research subjects related to the future Korean high performance rotorcraft.

• Journal of Aerospace System Engineering
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• v.3 no.1
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• pp.12-16
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• 2009

The laminated sequence and thickness of a composite structure is an important design parameter which affect the strength and impact damage. In this study, it was investigated the residual strength of carbon fiber laminate after impact damage by the experimental investigation. The tensile strength test and compressive strength test were used to find the mechanical properties, previously. Impact test was performed using low-velocity drop-weight test equipment. The impact damages were finally assessed by the compressive strength test. The investigation results revealed the residual strength of the damaged specimens due to the impact damage.

• Journal of Aerospace System Engineering
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• v.4 no.1
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• pp.23-26
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• 2010

In this study, it was performed damage assesment of small scale composite aircraft developing. This aircraft adopted the sandwich structure to skin of wing. This study aims to investigate the residual strength of sandwich composites with Nomex honeycomb core and carbon fiber face sheets after the open hole damage by the experimental investigation. The 4-point bending tests were used to find the bending strength, and the open hole was applied to introduce the simulated damage on the specimen. The bending strength test results after open hole was compared with the results of no damaged specimen test. The FEM analysis is assessed via an experimental 4-point bending test.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• v.2
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• pp.475-478
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• 2006

본 논문에서는 소형 무인항공기의 정확한 위치, 속도, 자세 정보를 제공하기 위해 저급의 MEMS IMU를 이용한 항법 시스템을 제안한다. 제안하는 시스템은 비행체의 직선운동과 회전운동을 측정할 수 있는 관성측정기와 위성신호를 수신하여 항체의 위치, 속도 정보를 제공하는 GPS 수신기, 지구 자기장 정보를 이용하여 방향각 정보를 제공하는 지자기 센서들로 구성되었다. SDINS와 약결합 방식의 칼만필터를 이용한 항법 시스템은 초기정렬 알고리즘과 센서 오차 보상 알고리즘, 자력계 보상 알고리즘 및 복합항법 알고리즘으로 나뉘며, 설계된 항법 알고리즘들은 시뮬레이션과 차량 실험을 통해서 성능을 분석하였다.

• Journal of the KSME
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• v.34 no.5
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• pp.326-333
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• 1994

신소재의 보편적인 정의는 "재료의 원료를 새로 개발하거나, 종래의 원료에 개선된 제조기술 또는 응용기술을 적용시켜 종래에 없던 우수한 특성, 기능을 갖게 하는 소재"라고 한다. 즉, 고 부가 가치의 금속, 세라믹스, 폴리머, 복합재료를 총칭하여 신소재 또는 첨단소재(advanced materials) 라고 하며, 산업기기의 중요한 기능소재로서 기계공업의 발전에 필수적이다. 1970년대부터 1980 년대 초반에 걸쳐 본격적으로 시작된 세라믹스에 관한 연구는 제조 및 사용분야 전반에 걸쳐 기술혁신을 가져왔다. 그후 천연 광석분말만이 아니라 새로운 화학적 방법으로 제조된 분말을 사용하여 창출된 재료라는 뜻으로 "뉴(new)세라믹스"라고 불려지거나, 개선된 제조기술을 통하여 재료의 섬세한 미세조직을 얻음으로 우수한 특성을 갖는 재료라는 뜻으로 "파인(fine)세라믹스" 등의 이름이 붙여지게 되었다. 이제 센서용 소재는 물론이고, 가위, 손목시계 케이스, 바이오 세라믹스 등에 이르기까지 10년 전보다 훨씬 다양하게 세라믹스를 사용한 물체를 발견할 수 있다. 이들 세라믹스 중 기계적, 또는 열 응력을 받는 구조물에 적용되는 것을 구조 세라믹 스(structural ceramics)라고 한다. 이 글에서는 차세대 자동차 및 항공기에까지 적용이 시도되고 있는 이들 구조세라믹스를 대상으로 하여 일반적으로 제조법, 응용분야, 연구동향 및 전망을 정리하고자 한다.조법, 응용분야, 연구동향 및 전망을 정리하고자 한다.

• Proceedings of the Korea Information Processing Society Conference
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• 2015.10a
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• pp.1844-1845
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• 2015

최근에는 지진의 발생 빈도가 높아지고 발생되는 재난의 규모가 점차 증가되고 있다. 무인항공기(Unmanned Aerial Vehicle, UAV)은 이동 속도가 빠르고 장착된 카메라로 감시가 가능하기 때문에 넓은 지역의 재난 상황을 모니터링하거나 발생 여부를 감시하기에 적합하다. UAV의 기능이 점차 증가되면서 이를 조종하기 위한 방법도 복합해지고 있기 때문에 전통적인 조종기 기반의 조종 방법이 아닌 새로운 형태의 사용자 인터페이스가 요구된다. 본 논문에서는 소방방재용 UAV를 제어하기 위한 사용자 인터페이스를 제안한다. 직관적인 사용자 인터페이스를 제공하기 위해서 체감형 인터페이스를 적용한다.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.254-262
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• 2008

Several decades have passed since tiltrotor technology became a hot issue of debates between aircraft majors, policy maker and mass-media. Although most of those subjects have been officially probed or answered in objective way, biased articles or argues related with the adequacy of this technology still prevail in the way of tilt-rotor development programs, which are totally irrelevant and out-dated. This paper aims to help understanding on those issues in technically balanced manner and the cases of flight test mishaps.

• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.52-59
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• 2019

The rotor blade is a key component that generates the lift, thrust, and control forces required for helicopter flight by the torque transmitted through the hub and the blade pitch angle control, and should be designed to factor vibration characteristics so that there is no risk of resonance with structural safety. In this study, the structural design of the main rotor blade for MPUH(Multi-Purpose Unmanned Helicopter) was conducted and the sectional stiffness measurement of the fabricated blade was performed. The evaluation of the vibration characteristics of the main rotor system was then conducted factoring the measured stiffness distribution. The interior of the rotor blade comprised of the skin, spar, and torsion box, and carbon and glass fiber composites were applied. The Ksec2D program was applied to predict the stiffness of blade, and the results were compared to the measured data. CAMRADII, a comprehensive rotorcraft analysis program, was applied to investigate the natural frequency trends and resonance risks due to the rotor rotation.