• Journal of Aerospace System Engineering
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• v.11 no.4
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• pp.1-7
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• 2017

The development of effective design allowable values for unmanned composite aircraft is an issue of paramount concern for the industry. The application of conventional manned aircraft structural certification methods to unmanned aircraft such as prototype and technology demonstrators, can lead to excessively long development time and costs. In this paper, the determining method of composite structure design allowable values for light composite unmanned aircraft is presented to reduce to the structural weight. This paper seeks to show the applicability of composite B-basis material values as a design allowable of light composite unmanned aircraft structures. A review of different civil and UAV targets failure probability is given. From the results, the researchers can know that the requirements of light composite unmanned aircraft design allowable should be alleviated, compared to manned composite aircrafts.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.30 no.5
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• pp.445-452
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• 2017

The wing leading edge skin in this research is an essential structural factor for improving wings' aeromechanical functions, protecting the interior elements of the wings from external damage including birds, and navigating planes safely. The study compared and reviewed models manufactured for optimal light-weight wings of composite UAVs. It compared and investigated displacement forms of torsion loads through finite element analysis using MSC. Patran/Nastran. By confirming the improvement of light-weighting performance according to lamination type, thickness change and shape through torsion strength tests of each model, the research suggested the optimal light-weight wing leading edge skin for small composite UAVs.

• Proceedings of the KIEE Conference
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• 2005.07b
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• pp.1583-1585
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• 2005

주요 대중교통 수단에 있어서 승객의 서비스 질 향상을 위한 연구가 활발히 진행되고 있다. 국내외적으로는 UIC, ISO, KS등에서 규격으로 제시되고 있으며 이에 부합하기 위한 일련의 연구가 진행되고 있다. 그러나 현재까지 국내에서는 무인 운전시스템이 없어 승차감 등은 운전자의 운전 조작의해 판단하였으나 무인 운전되는 고무차륜 AGT 경량전철 시스템을 개발함에 따라 ATO측면에서의 제어가 중요하게 부각되었다. 따라서 본 연구에서는 고무차륜 AGT 경량전철 시스템에 최초로 CBTC 을 적용하여 무인운전의 과정을 기술하였다.

• KIPS Transactions on Software and Data Engineering
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• v.6 no.9
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• pp.429-436
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• 2017

Unmanned Aerial Vehicles (UAV) that are piloted without human pilots can be commanded remotely via frequencies or perform pre-inputted missions. UAVs have been mainly used for military purposes, but due to the development of ICT technology, they are now widely used in the private sector. Teal Group's 2014 World UAV Forecast predicts that the UAV market will grow by 10% annually over the next decade, reaching $ 12.5 billion by 2023. However, because UAVs are primarily remotely controlled, if a malicious user accesses a remotely controlled UAV, it could seriously infringe privacy and cause financial loss or even loss of life. To solve this problem, a secure channel must be established through mutual authentication between the UAV and the control center. However, existing security techniques require a lot of computing resources and power, and because communication distances, infrastructure, and data flow are different from UAV networks, it is unsuitable for application in UAV environments. To resolve this problem, the study presents a lightweight UAV authentication method based on Physical Unclonable Functions (PUFs) that requires less computing resources in the ground Control and Non-Payload Communication (CNPC) environment, where recently, technology standardization is actively under progress.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.50-54
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• 2015

구형무인비행체는 다중 모터를 이용한 무인항공기에 비행 소형화, 경량화, 경제화 등의 장점을 가지고 있다. 본 논문에서는 구형무인비행체의 경로 추종을 위한 제어기 설계 및 성능에 대한 내용을 다루고 있다. 먼저 구형무인비행체의 운동방정식이 제어기 설계를 위해 유도되었고, 유도된 운동방정식을 이용해 경로 추종 제어기를 설계하였다. 구형무인비행체의 자세제어는 무게중심을 변화하는 방법을 사용하였다. 요구 경로를 설정하여 설계된 제어기의 경로 추종 성능을 MATLAB 시뮬레이션을 통해 확인하였다. 시뮬레이션 결과, 제시된 제어기가 설정된 경로를 추종하고 있음을 확인하였다.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.179-185
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• 2002

In this study, the structural design method for the modified long-endurance UAV is presented. Composite materials using room temperature curing method and wet lay up procedure is applied to all wing structures. The modified wing is composed of 3-piece component for improvement of ground handling. As the sandwich structure is efficient for light weight and high stiffness, all skin is used the sandwich consisting of glass/ epoxy fabric and balsa wood. The proof test is performed up to limit load corresponding to 4g load condition for the modified wing structure.

• Proceedings of the KIEE Conference
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• summer
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• pp.541-544
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• 2004

지난 99년 이후 친환경적이며 경제적이고 효율적인 대체 교통수단의 개발이라는 목표 하에, 차세대 근거리 교통수단으로 각광받고 있는 경량전철 시스템 적용을 목표로 무인 변전소 기반의 전력감시제어 시스템(SCADA)을 개발하였다. 차세대 변전소 기술 적용이라는 취지 하에 각종 IED들과의 연계는 모두 통신으로 처리하여 시스템의 고기능화를 추구하였고, Network 이중화를 통하여 시스템의 신뢰성을 제고하였으며, CCTV 및 각종 보안센서를 적용하여 배전반의 무인화 운전 및 원격 상시 감시 기능을 구현하였다. 이로써 신뢰성 있는 시스템 기반의 무인 변전소 기술 확립이라는 측면에서 현재 진행되고 있는 변전소 자동화 기술에 일조하며, 나아가 향후 에너지 IT산업기술의 기반이 되리라 사료된다.

• Composites Research
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• v.32 no.1
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• pp.45-49
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• 2019

Fiber reinforced composites fabricated by the resin film infusion (RFI) process, which is one of the outof-autoclave process, have the advantage of significantly reducing the processing cost in large structures while having excellent mechanical properties and uniform impregnation of the resin. In this study, we applied RFI carbon fiber composites to unmanned aerial vehicle structures to improve structural safety and achieve weight reduction. The tensile test results showed that the strength was 46% higher than that of generic T300 grade plain weave carbon fiber composites. As a result of the layup design and finite element analysis of the composite wing structure using the above material properties, the wing tip deflection is decreased by 31%, the structural safety factor is increased by 28% and the weight of the entire structure can be reduced by more than 10% compared to the reference model using glass fiber composite material.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.11
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• pp.908-914
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• 2013

This study has developed a small solar powered UAV and performed its flight tests. In daylight, a solar powered UAV flies by using some of electricity generated from solar cells, and stores the remainder into battery. At night it flies by using electricity from battery. A solar powered UAV should have aerodynamically efficient configurations, light-weight, strong wing and fuselage. Its electric propulsion system and solar power system should also be very efficient. In the present study the solar powered UAV and its solar power system are developed for 12 hour continuous flight and the flight tests are performed to verify its performance. The flight tests performed in fall and winter to prove the present solar powered UAV is successful in four-season 12 hour flight.

• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.36-42
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• 2019

This research illustrates how the simulation environment for operating the simultaneous man/unmanned aerial vehicle teaming is constructed. X-Plane program, HILS for the ducted fan aircraft (unmanned) and CTLS (manned aircraft) with communication devices are interfaced to simulate the basic co-operational flight. The X-plane and HILS can allow operators to experience the maned and unmanned aircraft operation in the airspace on the ground in turn they can perform various simulated missions in advance before the actual flight. For the test purpose, the data link between man/unmanned aircraft and ground control station is examined using C Band and UHF radio channels by the manned aircraft.