• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2019.06a
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• pp.264-266
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• 2019

드론에 프로젝터를 탑재한 드론 프로젝터 시스템을 활용한 이동형 프로젝션 디스플레이를 사용할 경우, 드론의 비행시 발생하는 흔들림이 그대로 프로젝터에 전달되기 때문에 프로젝터에 의해 투영된 영상에 왜곡이 발생하게 된다. 본 논문에서는 종래에 사용되던 드론의 비행정보 기반 투영영상 변환행렬을 실제 영상에 적용해보고 비행 움직임에 의해 발생하는 실제 투영영상에서 발생하는 오차를 평가하기 위한 방법을 제안한다.

• Proceedings of the Korean Society of Computer Information Conference
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• 2023.07a
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• pp.215-216
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• 2023

군사 목적으로 사용되던 드론이 일반 사용자를 위한 범용 드론으로 활용 분야가 확장됨에 따라, 국방 및 운송, 물류, 농업과 같은 다양한 분야에서 활용되는 실정이며, 이와 관련된 산업의 발전에 기여하고 있다. 그러나 급격한 발전으로 인하여, 드론의 안전성은 고려하지 못한 한계점이 존재하였고, 이는 드론에서의 다양한 보안위협으로 나타났다. 본 논문에서는 4차 산업 혁명 시대의 핵심 기술인 드론의 안전성을 향상시키기 위한 목적으로, 드론의 신규 취약점을 발굴하고 실증하였다. 실험을 위하여, 최근 출시된 G 제품을 대상으로, 드론에서 발생 가능한 다양한 취약점 중 하나인 GPS 스푸핑 공격을 시도하였으며, 실험 결과, GPS 좌표를 변조함으로써, 비행이 가능한 구역에서 비행 금지 구역으로 인식하도록 좌표를 조작하였으며, 비행 금지 구역으로 인식한 드론은 준비된 동작에 따라, 강제로 착륙시키거나 다른 장소로 이동시키는 것이 가능하다. 본 논문의 결과는 드론의 안전성을 향상시키기 위한 참고 자료로 활용될 것으로 사료된다.

• Proceedings of the ESK Conference
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• 1992.10a
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• pp.26-32
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• 1992

세계적으로 항공기 사고의 통계적 분석에 의하면 항공기 운용자의 인적과실(Human error)로 인한 항공기 사고가 약 70% 이상으로 보고되고 있다. 항공기 운용자의 인적과실에 기인한 요인들 중에서 운용자의 작업량, 작업공간, 작업환경, 인체크기, 인체 생리, 인간 심리 및 습관 등을 항공기 설계단계에서 고려하지 못한 요인이 대부분이다. 일반적으로 항공기 비행품질(Flying qualities)의 영향을 주는 설계분야는 크게 세가지로 항공기 형상(Configuration), 조종체계(Control system)및 조종실 배치(Cockpit layout)로 분류된다. 이들 세가지 설계분야 중에서 조종실의 운용자 인간공학적인 요구 사항을 고려하지 않으면 항공기 운용성 품질중에서 삼분의 일이 감소될 수 있다. 그리고 항공기 개발시에 전담하는 항공기 설계 분야별로 구분하고 그 전담설계 부서들과 인간공학적 조종실 설계 전담 부서가 항공기 비행 품질 및 운용자 인적과실(Human error)에 미치는 영향을 분석하고 인간공학의 중요성을 강조한다. 항공기를 개발할때에 개발자는 그 항공기를 운용하는 운용자의 인체, 생리, 심리, 습관 등을 고려 하여 항공기 조종실의 인간공학적 최적화 설계 및 배치 (Design and layout)를 개발초기단계부터 항공기를 설계할때에, 그 항공기의 조종실 품질은 조종사가 항공기 비행 임무를 수행할때에 항공기 비행을 위한 용이한 정보 인식(Sencing), 용이한 정보 결심(Deciding) 및 용이한 조종(Manipulating)의 특성을 조종사에게 제공할 때 항공기 비행 품질이 좋아질 것이다.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.123-130
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• 2008

Flight safety analysis, which includes risk estimation for the various abnormal flight modes in addition to normal flight, has to be performed necessarily to guarantee launch safety for the operation of space launch vehicles. For this purpose, a dedicated system has been developed such that all the necessary repetitive computations, result reports, and graphical presentations can be performed inside a single system for user convenience. In addition, the developed system is capable of representing computed results on a three dimensional Earth for the realistic presentation. The developed Flight Safety Analysis System will be employed for the launch operation of Korea Satellite Launch Vehicle-I.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.5
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• pp.448-454
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• 2008

This paper deals with a behavior based decentralized control strategy for UAV swarming utilizing the artificial potential functions and the sliding mode control technique. Individual interactions for swarming behavior are modeled using the artificial potential functions. The motion of individual UAV is directed toward the negative gradient of the combined potential. For tracking the reference trajectory of UAV swarming, a swarming center is considered as the object of control. The sliding-mode control technique is adopted to make the proposed swarm control strategy robust with respect to the system uncertainties and the varying mission environment. Numerical simulation is performed to verify the performance of the proposed controller.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.588-593
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• 2011

In this study, the performance analysis method for ramjet engine system with atmospheric air disturbance was proposed. Flight path was determined to satisfy dynamic pressure constant at each flight altitude. The atmospheric air disturbance incoming into a engine intake was simulated by the model Tank proposed. The performance parameters was investigated at each flight condition with air disturbance. Engine operation stability was evaluated as analysis of the normal shock position.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.411-413
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• 2009

This paper deals with supersonic vehicle. A supersonic vehicle has very complicated and high nonlinear thrust characteristics with respect to outer and inner environment during operation. For this reason, supersonic vehicle has many maneuver constraints and allows to operate within more narrow flight envelope. In this paper, trajectory optimization of supersonic vehicle is accomplished. The trajectory optimization problem is formulated by a discrete parameter optimization problem and the operation constraints are considered during trajectory optimization. It is shown that results of trajectory optimization give senses to fuel supply and nozzle throttle area control into effectiveness. Furthermore, general operation direction and its application for supersonic vehicles are discussed.

• Current Industrial and Technological Trends in Aerospace
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• v.6 no.2
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• pp.143-153
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• 2008

This paper describes the current research trend and future development direction of autonomous flight of the aircraft. The autonomous flight means that aircraft control system recognize and cope with the emergency situation confronted during the flight by itself. Current research for autonomous flight technology is mainly performed for the application to unmanned air vehicle. Considering advent of future air traffic management system and increasing demand of the unmanned air vehicle application, however, autonomous flight technology required to be combined with future air traffic management system. In this paper, the current air traffic management system and anticipating change in future air traffic management system was investigated and research activities of autonomous flight technology was described as well as future prospect.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.9
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• pp.57-64
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• 2004

The Purpose of this paper is to obtain the lateral-directional controllability and stability derivatives of the Velocity-173 from the flight test data and to simulate motion of the aircraft by using In-flight Real-Time Parameter Estimation Techniques. In this paper, the results of the In-Flight Real-Time parameter Estimation Techniques are compared with the results of the Advanced Aircraft Analysis. As a result, Estimation by using In-Flight Real-Time Parameter Estimation Techniques can be done rapidly and their results are reliable.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.243-253
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• 2014

This paper deals with the Quantitative Feedback Thoery(QFT) guaranteeing robustness in spite of the plant parametric uncertainty. In the frequency domain, the QFT guarantees the robustness of the design specification on the uncertainty of plant parameters and disturbance. In order to use the QFT, a selected plant is a Quad Rotor Vehicle(QRV) which has excellent maneuverability and possibility of vertical take-off and landing like the helicopter. And attitude control is examined the possibility satisfied the requirement specification under the setting parametric uncertainty of motors driving 4-blades. Additionally, in an attitude control, the pre-filter considering parameter range and operating range of a QRV was used. For these purpose, in this paper, by using QFTCT, that is the QFT Control Toolbox designing the controller in MATLAB by the QFT, each design phases are introduced.