• Journal of Aerospace System Engineering
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• v.15 no.1
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• pp.56-62
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• 2021

The purpose of this study was to address a Remote Airborne Control Simulator that could simulate manned-unmanned teaming (MUM-T mission) for fixed wing UAV. With rapid technological development of unmanned aerial vehicle (UAV), the mission capability of UAV has tremendously grown. The role of UAV extends from simple reconnaissance to highly automated wingman. Accordingly, the requirement of UAV ground simulator should be modified as well to meet function requirements for simulating a MUM-T mission. A developed remote airborne control simulator was developed for conducting fixed wing UAV MUM-T operation simulations on the ground. The newest MUM-T examples, usage, and application of the developed remote airborne control simulator for MUM-T simulation are also presented in this study.

• Proceedings of the Korean Society of Computer Information Conference
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• 2019.01a
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• pp.251-252
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• 2019

본 논문에서는 소형 무인항공체 (UAV, Unmanded Aerial Vehicle)가 제한된 공역 (airspace)에서 발생할 수 있는 상황을 예측할 수 있는 시뮬레이터를 개발하여 테스트를 수행한 결과를 보인다. 많은 소형 UAV가 밀집해서 비행하는 상황을 가정하여 충돌의 발생 가능성을 줄이기 위해 공역을 고도에 따라 계층으로 나누었으며 시뮬레이터에 이를 반영하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.1
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• pp.39-47
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• 2008

Automatic landing performance of UAV can be enhanced by adding Pseudolite(PL) to GPS. However, it is very hard to install and operate PL with confidence because GPS satellites are moving and the landing zone are usually changeable. The coverage and accuracy of combined GPS and PL can be estimated by using simulator and the correct information is very crucial to UAV operation. In this paper, design, implementation and evaluation of GPS/PL simulator for UAV landing are given. A very realistic coverage estimation is obtained using GIS data and ray launching method with considerations of the transmitter power level, altitude of UAV, number and location of PL. The expected accuracy is estimated using DOP and NSP computed using both GPS and PL. The performance of simulator is evaluated by comparing with the results of a real GPS receiver, and the certified simulator shows the required accuracy for UAV landing can be easily met by proper installation of at least 2 PLs.

• Journal of Computing Science and Engineering
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• v.2 no.4
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• pp.357-374
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• 2008

Over the past few decades, a considerable number of studies have been conducted on the technologies to build an UAV (Unmanned Aerial Vehicle) control system. Today, focus in research has moved from a standalone control system towards a network-centric control system for multiple UAV systems. Enabling the design of such complex systems in easily understandable forms that are amenable to rigorous analysis is a highly desirable goal. In this paper, we discuss our experimental evaluation of the Time-triggered Message-triggered Object (TMO) structuring scheme in the design of the UAV control system. The TMO scheme enables high-level structuring together with design-time guaranteeing of accurate timings of various critical control actions with significantly smaller efforts than those required when using lower-level structuring schemes based on direct programming of threads, UDP invocations, etc. Our system was validated by use of environment simulator developed based on an open source flight simulator named FlightGear. The TMO-structured UAV control software running on a small computing platform was easily connected to a simulator of the surroundings of the control system, i.e., the rest of the UAV and the flight environment. Positive experiences in both the TMO-structured design and the validation are discussed along with potentials for future expansion in this paper.

• Proceedings of the Korean Society of Computer Information Conference
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• 2018.07a
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• pp.299-300
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• 2018

개인 레저용, 상업용형 소형 무인 항공체 (UAV, Unmanded Aerial Vehicle)가 급증하는 상황에서 지상의 장애물과 법 규제 등으로 인하여 좁은 공간에 높은 밀도로 비행할 것이 예상 된다. 본 논문에서는 이런 상황에서 다수의 UAV가 비행 시에 발생할 수 있는 상황을 테스트를 위하여 Nvidia社의 PhysX 물리 엔진을 사용한 Unity3D를 이용하여 시뮬레이터를 개발한 결과를 보인다. 실제 비행 전 시뮬레이션으로 UAV의 이동 및 충돌여부, 병목현상 등에 대한 정보를 취득할 수 있도록 개발 하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.731-738
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• 2014

The mission of UAV has been expanded from a land to an ocean based on an enhancement of its technologies. Korea Aerospace Research Institute (KARI) also tries to expand the mission of tilt rotor UAV to an ocean, in which the shipboard landing of UAV is required. However the environment of an oceanic operation is severer than that of land due to salty, fogy, and windy condition. The landing point for automatic landing is not fixed due to movement of shipboard in roll, pitch, and heave. It makes the oceanic operation and landing of UAV difficult. In order to conduct an oceanic operation of tilt rotor UAV, this paper presents that the sea wave modeling according to the sea state is conducted and the shipboard landing of tilt rotor UAV under the sea wave is tested and evaluated through the flight simulator for UAV.

• Journal of the Korea Convergence Society
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• v.8 no.6
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• pp.9-16
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• 2017

Researchers are now faced with a limited flight time of the hoverable UAV due to the sluggish technological advances of the Li-Po energy density and try to find a bypassing solution for the fully autonomous hoverable UAV mission planning. Although there are several candidate solutions, automated wireless charging is the most likely and realistic candidate and we are focusing on the autolanding strategy of the hoverable UAV in this paper since it is the main technology of it. We developed a hoverable UAV flight simulator including Li-Po battery pack simulator using MATLAB/Simulink and UAV flight and battery states are analyzed. The maximum motor power measured as 1,647 W occurs during the takeoff and cell voltage decreases down to 3.39 V during the procedure. It proves that the two Li-Po battery packs having 22 Ah and connected in series forming 12S1P are appropriate for the autolanding mission planning.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.540-547
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• 2015

This paper describes development contents and flight tests of an ACMI simulator based on LVC integrating architecture. ACMI is the system that provides air combat training and ground bombing training for improving fighting efficiency, that is the live simulation involving real people to operate real systems. ACMI simulator was developed for technic acquisition of LVC interoperability by using data link communication. ACMI simulator simulated maneuvering of a fighter by operating an UAV, a fighter can be distinguished from an UAV by maneuvering characteristics. This study proposes maneuvering simulation method by using flight data of the UAV, and performed its flight test for verifying similarity of fighter maneuvering.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.4
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• pp.447-456
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• 2010

The application of a reliable motion simulator can contribute effectively in the evaluation of the performance of a vehicle platform in the development stage of a small unmanned aerial vehicle (UAV). Therefore, the research on a reliable motion simulator can accelerate the development of UAV and decrease the relevant cost. In this paper, the design factors considered in the preliminary design stage of a 6 degree-of freedom motion simulator are defined and the motion range of the simulator is described on the basis of these design factors. The length, acceleration, and the required thrust of actuators with respect to the motion simulator under development are also predicted. The motion range can be increased and a suitable actuator can be selected and produced by applying these results in the manufacturing process of the motion simulator. Thus, the reliability of the motion simulators can be achieved during the actual design operation of the UAV.

• 제어로봇시스템학회:학술대회논문집
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• 2004.08a
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• pp.969-974
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• 2004

For a maneuvering unmanned autonomous helicopter, it is necessary to design a proper controller of each flight mode. In this paper, overall helicopter dynamics is derived and hovering model is linearized and transformed into a state equation form. However, since it is difficult to obtain parameters of stability derivatives in the state equation directly, a linear control model is derived by time-domain parametric system identification method with real flight data of the model helicopter. Then, two different controllers - a linear feedback controller with proportional gains and a robust controller - are designed and their performance is compared. Both proposed controllers show outstanding results by computer simulation. These validated controllers can be used to autonomous flight controller of a real unmanned model helicopter.