• 한국항공운항학회지
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• 제24권4호
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• pp.6-11
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• 2016

There has been an increase in the number of researches on the segment for commercialization after developing avionics systems. In this paper, we have applied a commercial off-the-shelf(COTS) operating systems in an aircraft mission computer. We used UAV collision avoidance algorithms to compare the performance of COTS operating systems. The UAV collision avoidance algorithms were tested on different operating systems to compare the performances of the operating systems. The measured parameters are memory usage and processing time. We have verified that the UAV collision avoidance algorithms worked successfully and compared the performance of each operating system.

• 한국항공우주학회지
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• 제35권2호
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• pp.171-176
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• 2007

이동체와의 통신은 항상 안테나가 이동체의 방향을 지향하고 있어야 한다. 본 연구에서는 안테나가 이동체를 지향하기 위해서 사용되는 방식중 이동체의 위치를 측정하여 이동체와 안테나 사이의 기하학적 위치관계로부터 안테나의 지향각을 결정하는 방법을 사용하였다. 안테나와 무인항공기에 각각 GPS를 설치하여 각각의 위치를 측정하고 계산된 지향각을 향하도록 안테나를 구동하였다. 안테나의 지향각과 일치시켜 설치한 카메라를 사용하여 무인항공기를 촬영하여 추적 안테나 시스템의 성능을 검증하였다

• 제어로봇시스템학회논문지
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• 제20권11호
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• pp.1112-1117
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• 2014

Unmanned aerial vehicles (UAVs) are a popular research topic because of a great ripple effect in the future. However, current UAV technologies cannot be applied to manual aerial vehicles without any modification. As an alternative to current UAV technology, humanoid robots are adopted as pilots. If a humanoid robot controls an aerial vehicle autonomously, not only could manual aerial vehicles be utilized as UAVs, but the humanoid robot would also be put into an environment created for humans and conduct some missions suitable for humans. Humanoid robots are also able to handle tools and equipment designed for humans. In order to prove that a humanoid robot can pilot an airplane, an experiment is performed and the results of this experiment are shown in this paper.

• 제어로봇시스템학회논문지
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• 제18권5호
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• pp.433-438
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• 2012

In this paper, a operation network system equipped with onboard wireless communication systems and ground-based mission control systems is proposed for swarm flight of small UAVs. This operating system can be divided into two networks, UAV communication network and ground control system. The UAV communication network is intend to exchange the informations of navigation, mission and flight status with minimum time delay. The ground control system consisted of mission control systems and UDP network. Proposed operation network system can make a swarm flight of various UAVs, execute complex missions decentralizing mission to several UAVs and cooperte several missions. Finally, PILS environments are developed based on the total operating system.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.111-117
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• 2016

A new configuration of tiltrotor UAV previously suggested by Korea Aerospace Research Institute (KARI) for the purpose of increasing the endurance performance in airplane mode flight has extended wings attached to the nacelle and rotated with the nacelle according to the flight modes. In this research, the effectiveness of the extended wing on the enhancement of the endurance performance of KARI tiltrotor UAV (TR60) was analytically investigated based on CFD analysis results. Flight tests and ground tests of measuring the fuel consumption were also conducted to directly compare the endurance performance for the two configurations of TR60 baseline and TR60 extended-wing model.

• 제어로봇시스템학회논문지
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• 제14권5호
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• pp.502-510
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• 2008

UAVs(Unmanned Aerial Vehicles) have many applications in military and commercial areas. The flight control system of UAVs is more important than manned aircraft's because the mission of UAVs must be operated without a human pilot. But very heavy and expensive navigation system makes it difficult to develop UAV flight control system. In this research, GPS/IMU integrated navigation filter was developed for light weight/low cost flight control system of small UAVs. With this navigation filter, full flight control system which has real time operating capability has been developed. The performance of the flight control system is basically checked by HILSIM (Hardware In the Loop SIMulation). Finally, the flight control system is verified by showing performance test result under real flight environment.

• 항공우주기술
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• 제6권2호
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• pp.245-249
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• 2007

무인 항공기의 주요 목적은 유인 정찰기의 최대 단점인 조종사의 인명 손실을 제거하구 원하는 지역 또는 물체를 정찰하는데 두고 있다. 업무를 수행하기 위해서는 조종사 눈 역할을 할 수 있는 카메라가 필요하며, 획득한 정보 또는 목표물이 무엇인지를 구분하여야 한다. 본 보고서는 임무수행을 위한 영상감지장치의 선정에 필요한 요구 사항을 기술하였다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2014년도 추계학술대회 논문집
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• pp.189-192
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• 2014

Recently, development of electric powered UAV for high altitude and long endurance mission has been conducted worldwide. Long endurance requirement necessitates high lift over drag (L/D) aerodynamic characteristics and lightweight structures, leading to highly flexible wings with high aspect ratio. These highly flexible wings increase the danger of catastrophic aircraft failure due to flutter, which is a dynamic aeroelastic instability occurring from the interaction of aerodynamic, inertial, and elastic forces acting on the aircraft flying through the air. In this paper, flexible wing for electric powered UAV whose skin is fabricated using mylar film for lightweight design is briefly explained. In addition, flutter analysis procedures and results for the flexible wing in order to substantiate the aeroelastic stability requirements are presented.

• 한국항공운항학회지
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• 제12권2호
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• pp.17-28
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• 2004

In unmanned aerial vehicle (UAV), the high temperature results from friction with the air, combustion of fuel and combustion gas of a nozzle etc. It causes serious problems in the UAV structure. The characteristic analysis of heat resistant metal and ceramic materials and creep analysis for the functionally graded material (FGM) is presented in this paper. FGM is composed of two constituent materials that are mixed up according to the specific volume fraction distribution in order to withstand high heat condition. In addition, the creep behavior of FGM applied in duct structure of an engine is analyzed.

• 한국항공운항학회지
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• 제21권2호
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• pp.15-20
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• 2013

In order to set up the optimal required capabilities to satisfy a variety of domestic and foreign demands for the Tilt-rotor UAV, MOE(Measure of Effectiveness) hierarchy was designed through an expert discussion, and the weight of the MOE was determined by utilizing AHP method. The independent MOE assessment on the required capabilities was accomplished for the current configuration, available alternatives and foreign competitive UAVs. Finally the cost-effectiveness for the alternative and competition UAV was analyzed.