• 유체기계공업학회:학술대회논문집
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• 2006.08a
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• pp.415-421
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• 2006

The unsteady flow calculation around the proprotor of Smart UAV was conducted. Using the flight scenario of SUAV which composed of hover, transition, and airplane mode, the aerodynamic analysis of proprotor were performed for the variation of collective pitch, rpm, forward speed, and tilt angle. The unsteady compressible Navier-Stokes equations were used for the calculation and the dynamic overset grid technique was applied for the rotating proprotor. The aerodynamic performance of proprotor calculated in this way were validated by comparing with the performance data obtained from the blade element momentum method.

• 한국전산유체공학회:학술대회논문집
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• 2003.08a
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• pp.106-113
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• 2003

Smart UAV Development Program, one of the 21c Frontier R&D Program sponsored by MOST(Ministry of Science and Technology), was launched in 2002. As an air vehicle for the Smart UAV, CRW(Canard Rotor/Wing) concept was one of the candidates compared in trade-off study. The CRW concept has not only been proven completely but its aerodynamic characteristics not known in detail yet. Two calculation methods were adopted in this study to obtain aerodynamic data for the CRW. First method was the superpose DATCOM method which is capable of three lifting surfaces, and second one is the full Navier-Stokes computation around CRW configuration using overset grid method. Basic aerodynamic characteristics of the CRW configuration was analyzed and the minimum drag level with lift to drag ratio is presented. The peculiar flow characteristics around rotor/wing and hub were also examined and considered in the configuration design.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.49-60
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• 2008

In this technical paper, summarization of developmental results for the tilt-rotor SUAV Drive System being developed in the Smart UAV Development Center is carried out in view of design and analysis for the major components. The Drive System driving for the Rotor System of the SUAV is composed of very precise and advanced equipments, and also the applied technologies for development of the system had not ever experienced in the Korea. Therefore the collaboration study with an advanced company (EATI) in the USA performed in order to develop the SUAV Drive System.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.5-8
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• 2004

In this study, the fundamental design procedure for the Smart UAV fuel supply system was set up, and the preliminary design was peformed to meet the vehicle system requirements. The fuel system layout was determined through consideration of vehicle system requirements, and then fuel tank layout, design of components such as booster pump, jet pump, pipe, vent system, weight estimation, etc. were carried out.

• Korean Journal of Remote Sensing
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• v.36 no.5_3
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• pp.1013-1025
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• 2020

Unmanned Aerial Vehicle (UAV) platform is being widely used in disaster monitoring and smart city, having the advantage of being able to quickly acquire images in small areas at a low cost. Ground Control Points (GCPs) for positioning UAV images are essential to acquire cm-level accuracy when producing UAV-based orthoimages and Digital Surface Model (DSM). However, the on-site acquisition of GCPs takes considerable manpower and time. This research aims to provide an efficient and accurate way to replace the on-site GNSS surveying with three different sources of geospatial data. The three geospatial data used in this study is as follows; 1) 25 cm aerial orthoimages, and Digital Elevation Model (DEM) based on 1:1000 digital topographic map, 2) point cloud data acquired by Mobile Mapping System (MMS), and 3) hybrid point cloud data created by merging MMS data with UAV data. For each dataset a three-dimensional positional accuracy analysis of UAV-based orthoimage and DSM was performed by comparing differences in three-dimensional coordinates of independent check point obtained with those of the RTK-GNSS survey. The result shows the third case, in which MMS data and UAV data combined, to be the most accurate, showing an RMSE accuracy of 8.9 cm in horizontal and 24.5 cm in vertical, respectively. In addition, it has been shown that the distribution of geospatial GCPs has more sensitive on the vertical accuracy than on horizontal accuracy.

• 한국항공운항학회:학술대회논문집
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• 2006.05a
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• pp.136-139
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• 2006

• 한국항공운항학회:학술대회논문집
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• 2006.05a
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• pp.71-74
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• 2006

• 한국항공운항학회:학술대회논문집
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• 2005.05a
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• pp.120-123
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• 2005

• 한국항공운항학회:학술대회논문집
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• 2005.05a
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• pp.124-127
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• 2005

• 한국항공운항학회:학술대회논문집
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• 2005.05a
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• pp.112-115
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• 2005