• 전자공학회논문지CI
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• 제48권6호
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• pp.149-157
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• 2011

본 논문에서는 DPCM 기반의 새로운 비행데이터 전송방법을 제안한다. LRU에서 MC로 전송되는 비행데이터의 양은 항공기의 성능향상과 기능의 다양화로 인해 크게 증가되었다. 이는 MC에서 요구되는 Hard Real-Time 조건을 만족시키기 어렵게 한다. 이러한 문제를 해결하기 위해 X-Plane 시뮬레이터에 의해 생성된 비행데이터를 관찰하여 대부분의 비행데이터들은 완만한 변화를 보인다는 것을 확인하였다. 이 사실에 기초하여 ARINC-429 프로토콜의 수정을 통해 비행데이터의 차분 값을 전송하는 새로운 데이터 포맷과 기법을 제안 한다. 실험결과 기존의 ARINC-429 방법에 비해 20% 성능향상이 있음을 보였다.

• 한국항공운항학회지
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• 제27권2호
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• pp.54-69
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• 2019

The primary objective of this paper is to introduce the application of Human-Machine Interface (HMI) and Augmented Reality (AR) technologies in flight operations. These include: self-check-in, baggage handling, airport security and surveillance, airport operations monitoring, In-Flight Entertainment and Connectivity (IFEC), cockpit design, and cabin crew support. This paper investigates the application status and development trends of HMI and AR technologies for airports and aircraft. These technologies can provide more efficient in-flight passenger service and experience by using AR devices. This paper also discusses the developments such as; the Integrated Control Application (ICA) for the IFEC interface, AR flight simulation training program using the fixed-based simulator, and the AR aircraft cabin interior concept test program. These applications present how HMI and AR techniques can be utilized in actual flight operations. The developed programs in this paper can be applied to their purpose within aircraft interiors and services to enhance efficiency, comfort, and experience.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.52-56
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• 2004

Unmanned Aerial Vehicles (UAVs) are remotely piloted or self-piloted aircraft by inputted program in advance or artificial intelligence. In this study Aileron and Elevator are used to control the movement of airplane for horizontal and vertical flights about its longitudinal and lateral axis. In an introduction, the drone was linearly modeled by extracting aerodynamic parameter through flight test and simulation, lift and drag coefficient corresponding to angle of attack, changes of pitching moment coefficient. In the main subject, the flight simulation was performed after constructing hardware using TMS320F2812 from TI company and PID with lateral and longitudinal controller for horizontal and vertical flights. Flying characteristics of two system were estimated and compared through real flight test with hardware equipped algorithm and adaptive algorithm that was applied to consider external factors such as turbulence. In conclusion the control performance of the controller with proposed algorithm was streamlined at lateral and longitudinal controller respectively, we will discuss guidance command to pass way point.

• 한국항공운항학회지
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• 제18권2호
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• pp.23-34
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• 2010

After analyzing each procedure from standard instrument procedures used at Incheon International Airport, which is believed to have caused noise problems in and around Ganghwa island, we came to a conclusion that some Standard Instrument Departure Procedures and Standard Instrument Approach Procedures need to be revised, and therefore we made some propositions with regard to noise abatement procedures(CDA, RNAV approach etc.). Additionally, we evaluated viability of the proposed flight procedures by conducting a number of demonstrations with use of flight simulation.

• 한국멀티미디어학회논문지
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• 제20권6호
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• pp.865-872
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• 2017

Recent advance in electronics and scintillators makes it possible to utilize the time-of-flight (TOF) information in improving image reconstruction of positron emission tomography(PET). In this paper, we propose a TOF-based fast image reconstruction method for PET. The proposed method uses the deconvolution of TOF data for each angle view and the rotational averaging of deconvolved images. Simulation results show an improved performance of the proposed method, as compared with filtered backprojection (FBP) method, TOF-FBP, and TOF version of expectation-maximization(EM) methods. Simulation results also show a great potentiality of the proposed method in limited angle tomography applications.

• 전기학회논문지
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• 제64권7호
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• pp.1074-1080
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• 2015

In the last decades, the increasing interest in unmanned aerial vehicle(UAV) for military, surveillance, and rescue applications made necessary the development of flight control theory and body structure more and more efficient and fast. In this paper, we describe the design and performance of a prototype hexarotor UAV platform featuring an inertial measurement unit(IMU) based autonomous-flying for use in bluetooth communication environments. The proposed system comprises the construction of the test hexarotor platform, the implementation of an IMU, dynamic modeling and simulation in the hexarotor helicopter. Furthermore, the hexarotor helicopter with implemented IMU is connected with a micro controller unit(ARM-cortex) board. The P-PD control algorithm was used to control the hexarotor. We used the Matlab software to help us to tune the P-PD control parameters for quick response and minimizing the fluctuation. The control simulation and experiment on the real system are implemented in the test platform, evaluated and compared against each other.

• ETRI Journal
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• 제27권4호
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• pp.377-384
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• 2005

We investigate near-infrared light (NIR) propagation in a model of an adult head using an extensive Monte Carlo (MC) simulation. The adult head model is a four-layered slab which consists of a surface layer, a cerebrospinal fluid layer, a gray-matter layer, and a white-matter layer. We study the effects of a refractive index mismatch on the model, calculating the intensity of detected light, mean flight time, and partial mean flight time of each layer for various refractive indices of the cerebrospinal fluid layer as functions of source-detector spacing. The Monte Carlo simulation shows that the refractive index mismatch presents very rich results including rapidly decaying intensity of detected light and a peak and cross-over in the partial mean flight time with source-detector spacing. We also investigate spatial sensitivity profiles at various source-detector spacings, discussing the index mismatch effect on the model.

• 한국정보통신학회:학술대회논문집
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• 한국해양정보통신학회 2006년도 춘계종합학술대회
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• pp.139-142
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• 2006

Numerous simulation studies and researches have recently revealed the rapid development and evolution in the emerging area of intelligent unmanned aerial vehicle (UAV). This study aims to develop a flight performance evaluation about the wireless unmanned helicopter. The process includes the design and testing of flight hardware and software that interprets sensor data. For the unmanned helicopter used in this research, an inertial sensor that provides posture (roll, pitch and yaw angles) and a Bluetooth is used to provide wireless connection between the user's pc and the helicopter were installed in the helicopter the helicopter's pitch, roll and yaw were the communication data. The accuracy of the system was confirmed by a computer simulation. The software also has been developed to support operators and displays helicopter position and posture by graphics.

• 한국항공우주학회지
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• 제33권5호
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• pp.57-64
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• 2005

현대의 고성능 전투기에 탑재되어 있는 전기식 비행제어계통(Digital Fly-By-Wire Flight Control System)은 통합 다기능 감지기(IMFP : Integrated Multi-Function Probe)에 의해 항공기의 고도/속도/받음각 정보를 얻는다. T-50에 적용되어 있는 3개의 IMFP는 3중 결함 및 분리되지 않는 2중 결함에 대해서 비행 안정성(Flight Stability)을 확보하기 위해 형상 재구성 모드(Air Data Reconfiguration Mode)를 제어법칙에 적용했다. 본 논문에서는 항공기 운용 시 발생할 수 있는 IMFP 결함으로 인한 형상 재구성 모드 제어법칙에 대해, 비행 안정성을 해석하기 위하여 선형해석(Linear Analysis) 및 HQS( Handling Quality Simulator) 조종사 시뮬레이션을 수행하였고, T-50 비행시험 시, 발생했던 IMFP 결함으로 인해 제어법칙이 형상 재구성 모드로 적용되었던 사례를 제시했다. 그 결과, T-50 훈련기의 제어법칙이 형상 재구성 모드로 전환될 경우, 항공기 안정성에는 영향이 없다는 것을 알았다.

• 대한임베디드공학회논문지
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• 제15권3호
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• pp.149-157
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• 2020

Regarding previously-developed drone simulators, it was easy to check their flight stability or controlling functions based on the condition that their weight was fixed from the design. However, the drone is largely classified into two types that is the one with the fixed weight whose purpose is recording video with camera and racing and another is whole weight-variable during flight with loading the articles for delivery and spraying pesticide though the weight of airframe is fixed. The purpose of this thesis is to analyze the structure of drone and its flight principle, suggest dynamics-model-based simulator that is capable of simulating weight-variable drone and develop the simulator that can be used for designing main control board, motor and transmission along the application of weight-variable drone. Weight-variable simulator was developed by using various calculation to apply flying method of drone to the simulator. First, ground coordinate system and airframe-fixing coordinate system were established and switching matrix of those two coordinates were made. Then, dynamics model of drone was established using the law of Newton and moment balance principle. Dynamics model was established in Simulink platform and simulation experiment was carried out by changing the weight of drone. In order to evaluate the validity of developed weight-variable simulator, it was compared to the results of clean flight public simulator against existing weight-fixed drone. Lastly, simulation test was performed with the developed weight-variable simulation by changing the weight of drone. It was found out that dynamics model controlled various flying positions of drone well from simulation and the possibility of securing the optimum condition of weight-variable drone that has flying stability and easiness of controlling.