• 시스템엔지니어링학술지
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• 제6권1호
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• pp.25-32
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• 2010

The Test and Evaluation (T&E) process is an integral part of the Systems Engineering Process. The purpose of Test and Evaluation (T&E) in a system development is to identify the areas of risk to be reduced or eliminated. In this study, when develop aircraft of Civil Aviation with development experience of Military Aircraft, it is that establish Test and Evaluation process. Test and Evaluation for KC-100 small aircraft development can divide to certification test and development test. Certification test is proved compliance about Korea Airworthiness standard (KAS Part 23), through Development Test verify required performance of aircraft. These Test and Evaluation Process is more efficient and optimized.

• 항공우주산업기술동향
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• 제7권2호
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• pp.95-105
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• 2009

연료전지는 소음이 낮고$CO_2$ 배출이 없는 친환경적 특성을 기반으로 항공기 추진시스템에 적용되고 있으며, 현재 연료전지를 탑재한 여러 종류의 무인항공기와 소형 유인항공기 개발이 진행되고 있다. 항공기용 연료전지는 대표적으로 PEMFC(Proton Exchange Membrane Fuel Cell)방식과 SOFC(Solid Oxide Fuel Cell) 방식으로 분류되며, 항공기의 임무 및 운용조건에 적합한 연료전지 시스템이 개발되고 있다. 무인항공기의 경우 대부분 PEM 연료전지 기술을 기반으로 군용 또는 상용으로 활용할 수 있는 다양한 형태와 크기의 항공기가 개발되고 있으며, 시스템의 안정성과 운용시간이 더욱 향상될 것이다. 소형 유인항공기에서는 추진시스템을 연료전지로 대체하기 위한 많은 연구가 수행되고 있으며, 또한 대형 상용 항공기의 보조동력장치(APU)에 연료전지를 적용하여 성능을 높이기 위한 개발이 진행되고 있다. 향후, 연료전지항공기는 연료전지의 전력밀도 증가와 더불어 신뢰성과 효율을 더욱 향상시킬 것으로 기대된다.

• 제어로봇시스템학회논문지
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• 제20권11호
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• pp.1098-1102
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• 2014

Localization of aerial vehicles and map building of flight environments are key technologies for the autonomous flight of small UAVs. In outdoor environments, an unmanned aircraft can easily use a GPS (Global Positioning System) for its localization with acceptable accuracy. However, as the GPS is not available for use in indoor environments, the development of a SLAM (Simultaneous Localization and Mapping) system that is suitable for small UAVs is therefore needed. In this paper, we suggest a vision-based SLAM system that uses vision sensors and an AHRS (Attitude Heading Reference System) sensor. Feature points in images captured from the vision sensor are obtained by using GPU (Graphics Process Unit) based SIFT (Scale-invariant Feature Transform) algorithm. Those feature points are then combined with attitude information obtained from the AHRS to estimate the position of the small UAV. Based on the location information and color distribution, a Gaussian process model is generated, which could be a map. The experimental results show that the position of a small unmanned aircraft is estimated properly and the map of the environment is constructed by using the proposed method. Finally, the reliability of the proposed method is verified by comparing the difference between the estimated values and the actual values.

• 한국항공우주학회지
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• 제35권7호
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• pp.575-580
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• 2007

카나드 형상 고기동 항공기의 개념 설계 단계에서 높은 받음각 항공기 정적 안정성 분석을 위해 저속 소형 풍동시험을 수행하였다. 본 연구에서는 1/50축척의 일반적인 카나드-동체-날개 형상을 소형 풍동시험 모델로 사용하였다. 높은 받음각 비선형특성을 포함한 정적 안정성을 분석하기 위하여 카나드 굽힘에 따른 수직 꼬리 날개 효과를 분석하였다. 또한 높은 받음각에서 Nose Chine 효과를 분석하였다. 실험 연구에서 얻은 결과를 토대로 카나드 형상 항공기 높은 받음각 정적 안정성에 미치는 형상 변화 효과를 분석할 수 있었다.

• 시스템엔지니어링학술지
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• 제5권2호
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• pp.49-56
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• 2009

KC-100(KAI Civil Aircraft, Small Series) aircraft is 4 seats general aviation aircraft with single piston engine which is developing under FAA part 23 category by Korea Aerospace Industries(KAI) and will be a shadow program for civil aircraft safety infrastructure improvement. This aircraft will be the first civil aircraft developed in Korea meeting the Korean regulatory KAS Part 23 requirements. Type certification for KC-100 aircraft was applied at the second half of this year. The type certificate is expected to be issued after 3 years of design, prototype manufacturing, ground and flight tests. In this paper the system engineering process for civil aircraft was first reviewed. Next, the differences and similarities in the system development between military and civil aircraft were systematically examined using experiences for KAI military aircraft development program.

• 한국소음진동공학회논문집
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• 제15권6호
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• pp.718-723
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• 2005

The purpose of this study is to present a fundamental data for evaluating aircraft noise of building site development. By the field experiments and the predicted equal noise level contours using the INM program, actual condition in the building site development arranged district was investigated. In order to get the results, Analysis of factors effected on noise level, sound level on the rate of increase to aircraft demand and difference on the aircraft noise levels according to floor level in apartment house was carried out. As a result the influence of the take-off and landing direction were appeared greatly. The influences of the height at receiving point, movement number of aircraft and increase to aircraft demand were appeared small And the influence of 1 day average WECPNL must be considered.

• 한국항공운항학회지
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• 제23권1호
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• pp.96-102
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• 2015

Composite materials are widely used as structural materials for manufacturing an aircraft, due to their : low weight, low thermal expansion coefficient, production efficiency, anisotropy, corrosion resistance and long fatigue life. The range of using composite materials has been extended from the fuselage and the wings to the entire aircraft structure. In this paper, by analyzing the problems which were generated while designing and fabricating aircraft structures using composite materials, the differences between metallic structures and composite structures are described. In addition, the methodological improvement directions on design and fabricating are described.

• 한국전자통신학회논문지
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• 제9권9호
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• pp.1019-1025
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• 2014

최근 무인항공기(UAV : Unmanned Aerial Vehicle)에 대한 연구가 다양한 각도로 진행되어 군사용 비행체에 관한 연구에서 부터 민간용 비행체 및 일반 취미 활동용 비행체에 이르기까지 다양하게 연구가 진행되고 있다. 특히, 무인 소형 비행체에 대한 연구는 수직이착륙(VTOL : Vertical Take-Off and Landing)과 용이한 방향전환 및 정지비행(hovering)에 대하여 연구되고 있으며, 이러한 연구부분에 적합한 무인 소형 비행체가 쿼드로터(quardrotor)형 무인비행체를 중심으로 연구되고 있다. 이러한 무인 비행체에 대한 연구는 공기역학적 힘에 의해 부양되므로 복잡한 동역학 분석과정을 필요로 하고 있으며, 이러한 역학적 분석 및 실험적 모델을 바탕으로 제어기를 설계하고 있다. 본 논문에서는 일반적인 PID 제어기를 바탕으로 기본적인 자세제어를 구현한 후, 제어기 설계에 고려하지 못한 비선형적인 요소를 신경회로망(neural networks)의 강화학습(reinforcement learning) 알고리즘을 이용하여 일반적인 제어기 설계에 고려하지 못한 비선형적인 요소를 보완하여 보다 안정적인 쿼드로터의 자세제어 방안을 제시하고자 한다.

• 한국국방경영분석학회지
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• 제7권1호
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• pp.81-117
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• 1981

Mathematical models for hit probabilities of small arms are developed in order to estimate the expected hits on an aircraft for certain altitudes and air speeds. A model for the firing lead angle is developed for cases when the distribution of hits is normal and the firing angle is from 20 degrees to 160 degrees. probabilities of hit for single and multiple shots at various altitudes are calculated. Tables are given showing the probability of hits and kill for targets flying at high speed above 500 feet from ground level.

• 한국항공운항학회지
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• 제30권1호
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• pp.12-19
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• 2022

The exhaust wake of an aircraft engine is discharged in a high temperature and high speed, which can damage objects such as an aircraft in the rear. The exhaust wake can lift small foreign substances lying on the ground or falling off, and the floating foreign substances can enter the intake duct of the aircraft moving from the rear and cause engine FOD (Foreign Object Damage). This study experimentally analyzed how the engine exhaust wake generated from military jet fighters affects the movement of foreign substances and evaluated the effects of foreign substances on the damaged area by measuring wake velocity. The simulation and field experimental results confirmed that the effect of exhaust wake increases as the rear position closer, and that foreign substances lifted by the wake can act as FOD to the adjacent rear aircraft.