• Journal of Aerospace System Engineering
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• v.9 no.2
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• pp.19-24
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• 2015

Export basic trainer was designed to add armed configuration required by customer. Design configuration of main wing was changed to satisfy changed internal load caused by armed configuration. It was verified that design changed main wing airframe of export basic trainer satisfy the requirement through the structural detail analysis, structural ground test and flight test. This paper presents the durability test procensure and test result for the main wing of export basic trainer.

• Journal of the military operations research society of Korea
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• v.13 no.1
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• pp.19-27
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• 1987

This paper deals with the development of an expert system modeling by constructing a knowledge-based system of the dive recovery for anticrash on the ground or sea during the task of fighter aircraft. In an IBM PC / XT computer, a prototype dive recovery expert system is constructed using mu LISP-86 programming language, and is interconnected to the SAM SUNG RM-501 robot arm to test and simulate this model. The knowledge base of this model is composed of the dive recovery charts and the V-N envelope charts of F-4 D Phantom fighter aircraft. It is shown that the prototype expert system woks well and the feasibility of practical realization is valid.

• Journal of the military operations research society of Korea
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• v.24 no.1
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• pp.88-97
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• 1998

It is critical to determine the appropriate actions for safe landing of an aircraft in an emergency situation. An expert system can be very useful for this purpose. An expert system specifically for jet fighter $F-\bigcirc\bigcirc$ has been developed. Its knowledge base contains the standard procedures provided by various flight manuals and the expertise of human specialists such as pilots and emergency management personnels. Advising procedures are represented by an IF-THEN format in the developed rule-based expert system. Advises are provided in real time during the entire flight processes of ground, takeoff, inflight, and landing. The developed system would significantly increase the survivability of pilots and aircraft, while decreasing operational costs of emergency management personnels. By modifying the knowledge base, the developed system can also be applied to other types of aircrafts including civilian airlines.

• Proceedings of the Safety Management and Science Conference
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• 2011.04a
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• pp.445-450
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• 2011

본 논문에서는 항공기 정비 분야에서 paperwork와 현장-사무실의 구분된 작업에 Mobile device를 적용하여 직접적인 부품의 입/출고, 정비작업을 제외한 부분에서 인적오류 및 낭비가 발생하여 항공기의 AOG(Aircraft On Ground)가 길어짐에 따라 항공기를 사용하지 못하는 시간적 손해를 제거하여 정비 작업의 효율성을 높이는 방법을 제시하였다. QR code와 RFID, Tablet PC를 작업 대상 부품의 확인과 현장중심의 업무처리에 사용하였으며, 실시간으로 정비 진행 현황을 확인 할 수 있는 방법을 제시한 것이 본 연구의 특징이다. Arena 10.0으로 시뮬레이션을 구현하였고, 실제 자재보관창고와 hangar의 작업자와의 인터뷰를 통해 문제점 및 연구사항을 정의하였으며, 항공기 부품 중 바퀴를 대상으로 작업시간의 변화를 비교하였다. 시뮬레이션 결과 작업시간은 바퀴 한 개당 35.31분이 감소하였으며, 필요 작업 인원도 20%가 감소하였고, 정비 현장의 paperless를 달성하였다.

• Journal of Aerospace System Engineering
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• v.8 no.2
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• pp.33-39
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• 2014

Feathering spindle is one of the critical parts of the rotor system in the Smart Unmanned Aerial Vehicle(SUAV) that it was manufactured with special material, Maraging C300. During the initial ground and tie-down flight tests of the SUAV, surface of the feathering spindle contacting to the needle-roller bearings showed excessive wear and dent due to high vibrating loads transferred from the rotating blades. Gas nitriding process was applied to the bearing contact surface of the feathering spindle to increase surface hardness so as to improve the surface defects. This paper briefly presents the gas nitriding process adopted and the spindle quality improvements including wear and corrosion resistance.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.8-15
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• 2015

Unmanned Aircraft System(UAS) is a huge and complicated system that is composed of UAV, ground control system, datalink system, and mission equipments. We have applied system engineering to development of UAS. Configuration management is very important activity for efficient developments. The Configuration management process comprises four distinct disciplines (Configuration identification, Configuration control, Configuration status accounting, and Configuration audit). This paper explains the configuration management system of UAS development project which ADD executes and introduces several examples of these four disciplines.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.05a
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• pp.71-81
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• 1995

The Propulsion System Integration can be defined as the optimization technology of combining the propulsion system components with the airframe to achieve the overall aircraft misson performance goals. The disposition of propulsion system components on engine compartment enveloped by front fuselage and fire bulkhead is very restricted because of the interference with nose L/G and engine mountig strut. The design of components depends on the traditional technical data base. The engine satisfying a customer's ROC was selected among worldwide existing engines by the comparision studies of performance analysis with enigine installed effect, future growth potential, ILS, and application to aircrafts, etc. The ground test of the propulsion system integration was performed in the test cell and on the aircraft to assure the function of the components. The flight test was performed to confirm complying the performance requirements.

• Journal of Aerospace System Engineering
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• v.1 no.4
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• pp.22-27
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• 2007

The 150 gal Ion EFT(External Fuel Tank) used to enlarge the aircraft operation range was adopted an import equipment in T-50 FSD phase. But in Production phase the EFT was planed to develop for the stable ILS(Integrated Logistics Support) and technical ability improvement by using the composite materials. The design for configuration and fuel system is intended to maintain compatibility with aircraft systems and the development test is performed on component, assembly and aircraft. This study is conducted to provide the technology of design and test for the 150 gallon composite EFT in LRU level. The test results show that the composite EFT is satisfied with structural, functional and environment requirements which are described in specification.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.26 no.1
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• pp.1-9
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• 2018

Ground effect includes a reduction of induced drag, increase of lift, and nose-down moment during landing. These phenomena, occurring late in the landing maneuver, are considered to be of little significance because they tend to counteract and/or compensate in this respect. Even though it is unlikely to affect any flare profile variations appreciably, some pilots have reversed perception about such phenomenon and overestimate during landing. It is becoming a negative factor and is making an adverse effect on landing maneuver. This study examines the perception of ground effect of large aircraft pilots, reviews literature regarding ground effect, and makes suggestions that pilots can correctly recognize and respond to the effect during landing flare maneuvers.

• Korean Management Science Review
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• v.29 no.3
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• pp.183-192
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• 2012

For the past several decades, personnel scheduling and rostering problem has been one of the most popular research topics in optimization area. Among the numerous applications, airline (aviation) industry has been given most attention due to the economic scale and impact. Most of the literatures about the staff scheduling problem in airline industry are dealing with the air crew, pilots and flight attendances, and the rest of the literatures are about the ground staff, by whom cleaning, maintenance, fueling of aircraft and handling luggage are done from landing to taking off. None of the literatures found by the authors are dealing with the airline ground crew. In this paper roster of airline ground crew, who is responsible for issuing boarding pass, checking baggage, etc, is introduced, formulated and solved using CPLEX. Some expressions of the mathematical formulations, which are not suitable input format of the CPLEX, were transformed. Numerical examples are presented for the validation of proposed scheduling system.