• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.28 no.7
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• pp.509-518
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• 2017

Since the UAS(Unmanned Aircraft System) or Drone is expected to grow rapidly with the advent of the $4^{th}$ Industrial Revolution era, the EU, China, and Japan as well as United States have deveoped a national roadmap and actively fostered UAS related industries. Also, in Korea, the frequencies of 2,670 MHz bandwidth has been also supplied newly or additionaly in 2016 for Drones in order to activate promising a new UAS industry based on wireless communication, which has great potential for future industrial growth. Therefore, in this paper, some solutions to promote UAS industry has been proposed by analyzing the domestic trends, the major technologies, the frequency issues, and the law framework for UAS.

• Journal of the Korea Society of Computer and Information
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• v.24 no.6
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• pp.99-107
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• 2019

With the development of various types of military Unmanned Aircraft(UA)s, the need for interworking and integration between different platforms gradually increased. In order to ensure interoperability at each military UA System(UAS) level, North Atlantic Treaty Organization(NATO) has established STANAG-4586 "Standard Interfaces of Unmanned Aircraft(UA) Control Systems(UCS) for NATO UA Interoperability-Interface Control Document". This paper looks at the basic design structure of STANAG-4586 and the changes on Edition 4 to enhance joint operational capability through reflecting and updating the interoperability design of the military UAS. In particular, we analyze the enhanced Datalink Transition/Handover Procedure and Autonomous functions, one of the biggest features added to the edition. Through this, we propose a modification of UA data link exclusive control using UA Bypass structure, which was impossible in the one-to-one communication structure between existing UA and Core UCS(CUCS). We also suggest ways to improve UA operational reliability by applying Autonomous Functions that directly decides how to deal with emergency situations, rather than by a remote operator over CUCS.

• Journal of Institute of Control, Robotics and Systems
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• v.14 no.12
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• pp.1244-1252
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• 2008

This paper presents the analysis results obtained by the flight test of reconfiguration flight control system for an aircraft. The reconfiguration flight control system was designed by using control allocation scheme that automatically distributes the demanded control moments determined by control law to each actual control surface. In this paper, some control allocation algorithms for reconfiguration control of general aircraft with redundant control surfaces are summarized and their performance evaluation results through nonlinear simulation and Hardware-In-the-Loop-Simulation (HILS) test are shown. Also, Unmanned Aerial Vehicle (UAV) system adopted as a platform for the flight test of reconfiguration flight controller and the implementation procedure of reconfiguration flight controller into real-time UAV system were introduced. Finally, flight test results were analyzed.

• Journal of Advanced Navigation Technology
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• v.25 no.6
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• pp.510-516
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• 2021

Recently, the range of utilization and demand for unmanned aerial vehicle (UAV) has been continuously increasing, and research on the construction of a separate operating system for low-altitude UAV is underway through the development of a management system separate from manned aircraft. Since low-altitude UAVs also fly in the airspace, it is essential to establish technical standards and certification systems necessary for the operation of the aircraft, and research on this is also in progress. If the operating standards and certification requirements of the aircraft are presented, a test method to confirm this should also be presented. In particular, the accuracy of small UAV's navigation required during flight is required to be more precise than that of a manned aircraft or a large UAV. It was necessary to calculate a separate navigation error. In this study, we presented a test method for deriving navigation errors that can be applied to UAVs that have difficulty in acquiring long-term operational data, which is different from existing manned aircraft, and conducted verification tests.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.31 no.1
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• pp.11-17
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• 2023

In this study, the correlation analysis between total system error and environmental factor variables was performed to confirm the effect on the performance of the integrated navigation system by various environmental factors. To collect flight data of hybrid vertical take-off and landing UAVs, scenarios including various turning sections and straight sections such as left turn, right turn, turning rate, and path change angle were selected, and environmental data of wind direction, wind speed, temperature, air pressure, and humidity were collected in real time through weather station. As a result of the correlation analysis between the collected flight data and environmental data, it was concluded that the performance of the integrated navigation system by environmental factors within the collected data was not significant affected and was robust.

• Journal of Convergence for Information Technology
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• v.11 no.12
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• pp.97-105
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• 2021

Countries such as the United States, Russia, and Europe are developing and operating UAVs for various purposes, including stealth UAVs. North Korea is also operating unmanned aerial vehicles, and it is presumed that it is continuously flying south of the demarcation line to obtain information on the national security zone, but it is difficult to detect and neutralize it effectively. Therefore, this paper analyzed the military UAV development trends and military radar specifications in Western countries such as the United States and communist countries such as Russia, China, and North Korea through literature research. In addition, based on the investigation of the AESA radar-based UAV response system in the country, not only general responses but also countermeasures such as direct strike and electromagnetic pulses to North Korean UAVs that cannot be jammed were suggested.

• Advances in aircraft and spacecraft science
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• v.6 no.5
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• pp.371-389
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• 2019

The implementation of a robust $H_{\infty}$ Control, which is numerically efficient for uncertain nonlinear dynamics, on longitudinal and lateral autopilots is realised for a quarter scale Piper J3-Cub model accepted as an unmanned aerial vehicle (UAV) under the condition of sensor noise and disturbance effects. The stability and control coefficients of the UAV are evaluated through XFLR5 software, which utilises a vortex lattice method at a predefined flight condition. After that, the longitudinal trim point is computed, and the linearization process is performed at this trim point. The "${\mu}$-Synthesis"-based robust $H_{\infty}$ control algorithm for roll, pitch and yaw displacement autopilots are developed for both longitudinal and lateral linearised nonlinear dynamics. Controller performances, closed-loop frequency responses, nominal and perturbed system responses are obtained under the conditions of disturbance and sensor noise. The simulation results indicate that the proposed control scheme achieves robust performance and guarantees stability under exogenous disturbance and measurement noise effects and model uncertainty.

• Journal of Convergence for Information Technology
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• v.9 no.9
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• pp.141-146
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• 2019

The aircraft noise analysis area in this study is a training airfield where various kinds of aircraft are operated. It is difficult to identify the noise analysis as a real measurement in a training airfield. In order to overcome these practical limitations and to establish appropriate noise countermeasures, a noise map is prepared using the Integrated Noise Model Version 7.0 of the aircraft noise prediction program used by the FAA. The noise of C90GT aircraft was measured while flying the takeoff route, landing route, and long route. We want to identify areas where noise damage is more than 70 WECPNL. No area exceeding the legal standard of 70 WECPNL was found in all routes.

• Journal of the Korea Institute of Military Science and Technology
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• v.26 no.3
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• pp.302-312
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• 2023

This paper describes the analysis of lightning strike zoning, the indirect lightning data simulation and the protection design for lightning indirect effects of equipment by lightning strike for unmanned aircraft consisting of composite wings. Through the analysis of lightning strike zoning according to the external shape of unmanned aerial vehicles, the structure areas that should be protected during lightning strike is derived, and the protection requirements of lightning indirect effects for flight critical equipments and equipment that must be operated upon lightning strike was derived. Lightning protection levels according to the location of mounting equipment and surrounding structure materials for each equipment was derived, and the protection design of the unmanned aerial vehicle with composite structures was also proposed from direct effect of lightning. Later, the lightning protection technology will be verified by the ground test of lightning direct and indirect effects.

• Aerospace Engineering and Technology
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• v.13 no.1
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• pp.1-9
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• 2014

Goheung aeronautical center is located in the area of Goheung of which land is reclaimed from sea and has a runway of length 700m, width 25m with test facility which has been used for flight test of UAV and small aircraft. To support the enhancement of aircraft safety, 1090ES ADS-B ground system as the ground surveillance system has been implemented. ADS-B system based on GPS and digital data link provides the function of enhancing the aircraft safety through flight information among aircrafts. This paper gives the result that the implementation of ADS-B ground system and the flight test with onboard ADS-B transmitter has been conducted.