• The Journal of Aerospace Industry
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• s.66
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• pp.17-44
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• 2003

항공기의 이륙단념(Rejected Takeoff) 사고는 흔히 발생하지는 않지만, 발생하면 큰 사고로 이어지는 경우가 대부분이다. 제트기에 의한 운송서비스가 본격적으로 시작된 1959년부터 2000년 까지의 이륙단념 사고사례를 조사해 본 결과 총 94건이 발생했다. 사고사례 모두가 활주로 이탈로 이어졌고, 그 주요 원인은 이륙결심 속도를 넘어서 조작을 시작했기 때문이라고 미국교통안전위원회(NTSB)에서 발표하였다. 이런 결과는 미국 항공우주국(NASA)의 준사고보고제도(ASRS)에서 조사한 자료에도 비슷한 결과가 나온 바 있다. 따라서 항공기 운항의 기준이 되는 항공기 비행규정(Airplane Flight Manual)을 만들 때 적용하는 미국연방항공법(FAR)상의 이륙단념 전환시간이 국내 현장조종사에서도 적합한 지에 관해 연구하였다.

• Journal of Advanced Navigation Technology
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• v.10 no.4
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• pp.299-305
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• 2006

DURUMI-II is developed into test bed airplane for the multi-purpose flight test. It satisfied the civil aeronautics law. DURUMI-II is equipped with Airborne System for acquiring of flight test data and can fly by oneself. In this paper, the redundancy of DURUMI-II control system is operated sequentially is explained. The divided control surface and the requiring program method for flight test are described. Also, it is described that the exact control input is applied using the new method. Finally, the results of flight test for new method are analyzed.

• Journal of the Korean Institute of Electrical and Electronic Material Engineers
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• v.18 no.2
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• pp.153-158
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• 2005

Recently, as the feasibility study shows that trans-Korea railway and trans-continental railway are advantageous, interest in high-speed railway system is increasing. Because railway vehicle is environment-friendly and safe compared with airplane and ship, its market-sharing increases gradually. KHST(Korean High Speed Train) has been developed by KRRI (Korea Railroad Research Institute) for last 6 years to satisfy the need. An electric railway system is composed of high-tech subsystems, among which main electric equipment such as transformers and converter are critical components determining the performance of rolling stock. We developed a measurement system for on-line test and evaluation of performances of KHST. The measurement system is composed of software part and hardware part. Perfect interface between multi-users is possible. A now method to measure temperature was applied to the measurement system. By using the system, fault diagnosis and performance evaluation of electric equipment in Korean High Speed Train was conducted during test running.

• International Journal of Aeronautical and Space Sciences
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• v.2 no.1
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• pp.103-109
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• 2001

Productivity enhancement program of wind tunnel testing has begun at Korea Aerospace Research Institute Low Speed Wind Tunnel (KARI LSWT). A previous test record of a canard airplane model was adopted to examine the current status of wind tunnel testing efficiency. The time consumed to perform testing activities from the model preparation to data collection was broken down and the results were compared with those of the recent Boeing low speed test result. The efforts to improve the wind tunnel productivity consisted of the installation of mini crane underneath of test section, fabricating lift device for image fairings, model configuration changing rigs and the modifications of external balance system. Time reductions for changing strut interface platform and installation of image fairings. These effects showed more than 70% improvement over the previous test time. Integration of the new and modified systems will improve productivity of wind tunnel testing in KARI LSWT.

• International Journal of Aeronautical and Space Sciences
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• v.1 no.2
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• pp.68-74
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• 2000

A comparative wind tunnel testing of an airplane model was performed at the Korea Aerospace Research Institute Low Speed Wind tunnel(KARI LSWT). The model used for the comparative test was a seaplane model from the Glenn L. Martin Wind(GLM) Tunnel of University of Maryland, U.S.A. The 6-component external balance used in force and moment measurement is pyramidal type, which is a precision device that has strain gauge-type load cell inside of balance and the virtual center of the balance coincides with the tunnel centerline. Image method is adopted to eliminate the tare and interference of the model support, and to correct the flow angularity to the model also. Test results from KARI LSWT were compared with the results from GLM tunnel.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.424-424
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• 2000

The implementation of a insect-based flying microrobot has been previously proposed as using magnetic force. The flying principle of a butterfly is different from that of a airplane, which obtain lifting force above the wings by a air stream with low pressure. Butterflies obtain lifting force below the wings by flapping. They can fly when drag during the down stroke is greater that during the up stroke. The structure of flying microrobot must satisfy these condition. And that must be manufacture lightly and keep balance for rising to the air sufficiently. Moreover the efficiency of an electromagnet is high and the flux density is sustained uniformly and widely Nevertheless these condition is satisfied, the implementation of a flying microrobot is very difficult as the flying microrobot has to fly without guides or sensor. We propose differently a new model il] comparison with that other paper has suggested. This imitates the form of the Korean shield-shaped kite.

• Transactions of Materials Processing
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• v.18 no.3
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• pp.251-255
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• 2009

Since fastener bolt for airplane require high specific strength and corrosion resistance, Ti-6Al-4V alloy is widely used. However, the Ti-6Al-4V bolt is generally manufactured by cutting and rolling because of their poor workability. The aim of present work is to develop hot forming technology for high strength Ti-6Al-4V. Various heat-treatments were applied to specimen in order to increase hot-workability and prevent galling with die. Multiple forging were simulated with FE code to determine optimum process parameters including specimen temperature, strain rate, local strain, and thermal shrinkage. Forged samples were heat-treated again to increase their mechanical properties.

• Journal of the Korean Society for Precision Engineering
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• v.20 no.2
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• pp.136-145
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• 2003

The integrity of stiffened panels with stringers in airplane structure is generally enhanced by investigating the fatigue crack propagation behavior in detail and providing the technical methodology to deal with the propagating crack. This paper attempts to clarify the effect of load-ratio on the fatigue crack propagation rate and the fatigue life for the thin aluminum 2024-T3. Both the variable and the constant fatigue loading conditions are considered for the fatigue crack propagation behavior in stiffened panels with stringers.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2002.10a
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• pp.300-303
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• 2002

In recent days the more use of CFRP composite is in the airplane, and sport goods, etc., the mote necessity of research on it in this engineering. In this research, the CFRP composite specimen are fabricated by 48 CFRP plies with 6 orientation angles. and the specimens are drilled with 4tools The results are analyzed with consideration of cutting force, type of tools and fabrication condition. The specimens with each drilling conditions are also investigated with SEM. The optimal drilling conditions such as drill types and cutting force with respect to the fabricating condition are studied.

• Transactions of Materials Processing
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• v.6 no.4
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• pp.291-299
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• 1997

This paper is concerned with the design of process sequence to form the inner skin of landing gear. The inner skin of landing gear is a part of airplane which is known to be difficult to form its shape. Our study investigates the production method of inner skin and examines the design criteria by three dimensional elastic-plastic finite element method. Based on the results of simulation, design strategy for improving the process sequence is developed using stretch forming process. The final product of inner skin is produced in multi-stage operations with annealing treatment to meet the required capacity of press. The numerical results show that the newly designed process can produce the required part successfully within the design criteria.