• 대한토목학회논문집
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• 제40권5호
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• pp.521-526
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• 2020

활주로 및 유도로 등의 비행장 포장체는 고정익 항공기의 원활한 이착륙을 위해 반드시 필요한 시설물로 군에서도 전·평시 항공작전의 수행을 위해서 가장 중요한 시설물이라 할 수 있다. 따라서 전시에 이러한 시설의 피해를 줄이고 최단시간에 복구하는 것이 필요하다. 최근의 공격양상은 대형 폭발구를 조성하기 위한 고폭탄을 사용하기 보다는 적의 비행장을 효과적으로 공격하고자 정확도와 관계없는 다탄두 무기체계를 사용하는 것으로 변화되고 있다. 따라서 본 연구에서는 다탄두 무기체계에 적용된 탄두의 제원과 구성을 통해 현재 군에 설치된 활주로 및 유도로 등에 접촉하여 폭발이 이루어졌을 때 포장체의 방호성능 및 피해양상을 확인해 보았으며, 다탄두 무기체계는 광범위한 피해를 줄 수 있지만 각각의 탄두의 파괴력은 그리 크지 않으므로 이러한 공격 대한 최소한의 방호를 위해서 필요한 비행장 포장체의 설계 방안을 제시하고자 한다.

• 한국환경과학회지
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• 제22권7호
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• pp.823-836
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• 2013

Emissions of air pollutants and greenhouse gases (GHGs) from aircraft activities at 11 small-scale airports were investigated using the emissions and dispersion modeling system (EDMS) version 5.1.3 during the two year period of 2009~2010. The number of landing and take-off (LTO) at these airports was dominant for the aircraft type B737, accounting for more than 60% of the total LTOs. Out of the 11 small-scale airports, Gwangju (GJ, RKJJ) airport was the largest emitter of air pollutants and GHGs, whereas Yangyang (YY, RKNY) airport was the smallest emitter. The emissions of $NO_x$ and VOCs in 2010 at the 11 airports ranged from 1.9 to 83 ton/y and 0.1 to 17 ton/y, respectively. In 2010, the emissions of $CO_2$ ranged from 394 to 21,217 ton/y. The emissions of most air pollutants (except for $NO_x$ and $PM_{10}$) and GHGs were estimated to be the highest in taxi-out mode. The highest emissions of $NO_x$ and $PM_{10}$ were emitted from climb-out and approach modes, respectively. In addition, the total LTOs at the 11 small-scale airports accounted for the range of 9.3~9.9% of those at four major international airports in Korea. The total emissions of air pollutants and GHGs at the 11 airports ranged from 4.8 to 12% of those at the four major airports.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• 한국해양공학회지
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• 제28권5호
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• pp.411-422
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• 2014

A helideck is a very valuable offshore structure for the take-off and landing of a helicopter. In order to design a helideck, the design parameters and various loads defined by the regulations related to the design of a helideck should be applied. In this study, a risk analysis was performed based on the helicopter accidents for seven years, and the frequency and possible reasons for accidents involving helidecks were investigated. In addition, a finite element analysis of a steel helideck mounted on the upper deck of a ship (shuttle tanker) was performed with the load that should be considered when designing a helideck. Based on the results, a parametric study of helideck was carried out by applying a variety of design parameters, and an improved helideck design was presented. This improved helideck reduced the steel used by up to 24% compared to the initial helideck design, and the results of a finite element analysis were analyzed and compared with those of the initial analysis.

• 로봇학회논문지
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• 제18권1호
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• pp.1-9
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• 2023

This paper presents an optimal path planning strategy for aerial searching and surveying of a user-designated area using multiple Unmanned Aerial Vehicles (UAVs). The method is designed to deal with a single unseparated polygonal area, regardless of polygonal convexity. By defining the search area into a set of grids, the algorithm enables UAVs to completely search without leaving unsearched space. The presented strategy consists of two main algorithmic steps: cellular decomposition and path planning stages. The cellular decomposition method divides the area to designate a conflict-free subsearch-space to an individual UAV, while accounting the assigned flight velocity, take-off and landing positions. Then, the path planning strategy forms paths based on every point located in end of each grid row. The first waypoint is chosen as the closest point from the vehicle-starting position, and it recursively updates the nearest endpoint set to generate the shortest path. The path planning policy produces four path candidates by alternating the starting point (left or right edge), and the travel direction (vertical or horizontal). The optimal-selection policy is enforced to maximize the search efficiency, which is time dependent; the policy imposes the total path-length and turning number criteria per candidate. The results demonstrate that the proposed cellular decomposition method improves the search-time efficiency. In addition, the candidate selection enhances the algorithmic efficacy toward further mission time-duration reduction. The method shows robustness against both convex and non-convex shaped search area.

• 한국통신학회논문지
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• 제32권11A호
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• pp.1206-1212
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• 2007

국제민간항공기구(ICAO . International Civil Aviation Organization)는 항행안전시설의 일종인 전방향표지시설(VOR : VHF Omni-directional Range)을 1949년 국제표준 항법시스템으로 정하여 각국에서 항공로 구성과 항공기의 이착륙 유도에 활용할 수 있도록 하고 있다. 현재 VOR은 우리 나라의 39대를 포함하여 전 세계적으로 2,000여대가 설치되어 있어 가장 유용하게 활용되고 있는 항법시스템이며, 설계방식에 따라 크게 CVOR(Conventional VOR)과 DVOR(Doppler VOR)로 구분된다. 그러나 VOR은 VHF 반송파를 진폭 및 주파수 변조하여 항법정보를 제공하므로 주변 장애물에 의한 영향을 많아 예상하지 못한 성능 미흡으로 이미 설치한 장비를 옮기는데 따른 비용과 시간이 많이 소요되어 큰 사회적인 문제를 야기하기도 한다. 이 논문에서는 CVOR과 DVOR의 성능을 항공기를 이용한 비행측정으로 비교 분석하여 어느 VOR이 산악지대 등 주변에 장애물이 많은 우리나라에서 유용하게 사용될 수 있는지 제시함으로써, 향후 VOR의 설치장소 결정에 활용할 수 있도록 하여 성능 미흡으로 장소를 이전하는 등의 문제점을 해소하는데 도움을 주고자 한다.

• 한국수소및신에너지학회논문집
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• 제23권4호
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• pp.300-309
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• 2012

Long endurance is a key issue in the application of unmanned aerial vehicles. This study presents feasibility test results when fuel cell system as an alternative to the conventional engine is applied for the power of the UAV after the 150W fuel cell system is developed and packaged to the 1/4 scale super cub airplane. Fuel cell system is operated by dead-end method in the anode part and periodically purged to remove the water droplet in flow field during the operation. Oxygen in the air is supplied to the stack by the two air blowers. And fuel cell stack is water cooled by cooling circuit to dissipate the heat generated during the fuel cell operation. Weight balance is considered to integrate the stack and balance of plant (BOP) in package layout. In flight performance test, we demonstrated 4 times standalone take-off and landing. In the laboratory test simulating the flight condition to quantify the energy flow, the system is analyzed in detail. Sankey diagram shows that electric efficiency of the fuel cell system is 39.2%, heat loss 50.1%, parasitic loss 8.96%, and unreacted purged gas 1.67%, respectively compared to the total hydrogen input energy. Feasibility test results show that fuel cell system is high efficient and appropriate for the power of UAV.

• 한국항행학회논문지
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• 제22권6호
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• pp.522-529
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• 2018

FOD는 항공기에 위험을 줄 수 있는 위험요인을 지닌 각종 금속, 비금속의 이물질을 총칭한다. FOD는 활주로 및 유도로, 정비시설 등 특정구역 및 시간을 가리지 않고 발생하며, 항공기의 이동 및 이착륙 시 항공기의 안전에 치명적인 위험을 내재하고 있다. 이에 활주로 내 FOD 발생 시 신속하고 효과적인 탐지 및 제거가 필요하다. 최근 항공 안전 기술 개발의 일환으로 공항 내 활주로 이물질 자동 탐지 시스템 개발이 진행 중에 있다. 본 논문에서는 한서대학교 태안캠퍼스에서 EO/IR 카메라 및 레이더를 이용한 이물질 자동 탐지 실험을 진행하여 주야간 정상적으로 탐지되는 것을 확인하였다.

• 한국항행학회논문지
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• 제28권3호
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• pp.300-308
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• 2024

도심 항공 모빌리티(UAM)는 도시의 교통 혼잡과 환경 문제에 혁신적인 해결책을 제공하는 새로운 교통수단으로 부상하고 있다. 특히 전기수직이착륙(eVTOL) 항공기를 통해 도심 내 이동성을 향상시키고 교통 혼잡을 감소시키며 환경오염을 줄이는 데 기여할 것으로 기대된다. 그러나 UAM 시스템의 성공적인 구현과 운영은 센서 기술과 같은 고도로 발전된 기술적 인프라에 의존을 많이 하게 된다. 이러한 센서 기술 중에서도 3D LiDAR (light detection and ranging) 시스템은 복잡한 도심 환경에서 비행체가 장애물을 감지하고 경로를 생성하는 데 필수적이다. 본 논문은 3D LiDAR를 이용한 객체 검출 기능의 중요성과 성능을 중심으로 LiDAR 기반 인지 솔루션 개발의 도전 과제에 초점을 맞추며, LiDAR 데이터 처리 알고리즘과 객체 검출 방법론을 통합하여 비행체의 안전 운항에 기여하는 인지 솔루션의 효과를 실험적으로 검증한다.

• 산업경영시스템학회지
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• 제39권3호
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• pp.56-63
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• 2016

For air express service providers offering various express delivery services such as overnight delivery and next-business day delivery services, establishing quickly cargo loading plans is one of important issues owing to the characteristics of air express business, i.e., a short amount of time is available to complete all cargo loading operations before flight departure after receiving air express containers, pallets and bulks. On the other hand, one of major concerns in the air cargo loading planning is to make a plan that insures the stability of an aircraft to avoid take-off, flight, and landing accidents. To this end, this paper considers an air cargo loading planning problem, which is the problem of determining locations in the aircraft cargo space where air containers, pallets and bulks to be loaded while insuring the aircraft stability, motivated from DHL and Air Hong Kong. The objective of the problem is to maximize the total revenue gained from loading air express containers, pallets and bulks. To solve the problem, this paper suggests a simulated annealing algorithm to overcome impracticality of the integer programming model developed by a previous study requiring excessive computation time. The results of computational experiments show that the heuristic algorithm is a viable tool for establishing express cargo loading plans as giving robust and good solutions in a short amount of computation time. Scenario analyses are performed to investigate the effect of the current activities of air express carriers on the revenue change and to draw practical implications for air express service providers.