• 한국항공운항학회지
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• 제11권2호
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• pp.93-107
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• 2003

This study is performed to secure the safety of civil aviation by establishing systematic analysis ability of Flight Data Recorder. Through this study, readouting UFDR(Universal Flight Data Recorder) to personal computer, flight data numerical analysis and regulations of Missed Approach. In the analysis, the flight data of B747-400 model aircraft with Missed Approach in San Francisco(KSFO) was selected.

• 한국항공운항학회지
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• 제10권1호
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• pp.21-34
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• 2002

This study is performed to secure the safety of civil aviation by establishing systematic analysis ability of Flight Data Recorder. Through this study, downloading SSFDR(Solid State Flight Data Recorder) to personal computer, editing interface file, flight data numerical analysis and regulations relayed to the aircraft with changes in destination airport in flight are performed. In the analysis, the flight data of B747-400 model aircraft between Los Angeles(KLAX) and Jeju(RKPC) was selected.

• 한국항공운항학회지
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• 제13권2호
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• pp.27-34
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• 2005

This study is performed to analyze the turbulence distribution of Fev. & Mar. in 2000 by the analysis of the parameters related with flight data of FDR(Flight Data Recorder). In the analysis, we selected the Solid State Flight Data Recorder(SSFDR) & Universal Flight Data Recorder(UFDR) flight data of the exact same aircraft(capacity 120 persons). Through this study, we verified that turbulence is concerned with configuration of the ground and flight situation of aircraft.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.56.6-56
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• 2001

The FDAS(Flight Data Analysis & Animation System) is a comprehensive analysis system designed for the improvement of flight safety. FDAS provides decoding, analysis and animation tools that can be used for investigation of data origination primarily from Flight Data Recoders(FDRs), Quick Access Recoders(QARs), Using FOQA(Flight Operation Quality Assurance) Data Analysis, an analyst can perform a variety of functions including data smoothing, interpolation, differentiation, integration, calculator function, flight path generation, performance routines, as well as user-programmed functions. Utilizing data captured and processed by our FDAS software module, FDAS provides high-fidelity 3-D aircraft views and instruments views. Multiple windows enable you to view the situation from a variety of perspectives, including out-of-window, chase plane ...

• 항공우주시스템공학회지
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• 제15권6호
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• pp.42-49
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• 2021

To develop a high-resolution electro-optical/infrared (EO/IR) payload to be mounted on a high-speed and performance fighter aircraft in an external POD for acquiring daytime and nighttime image information on tactical targets, simulations, including flight environments and maneuvers, should be performed. Such simulations are pertinent to predicting the performance of several variables, such as aerodynamic force and inertia load acting on the payload. This paper describes the development of a flight data acquisition and analysis system based on flight simulation software (SW) for mission simulation of super-maneuverability fighter equipped with EO/IR payload. The effectiveness of the system is verified through comparison with actual flight data. The proposed flight data acquisition and analysis system based on FlightGear can be used as an M&S tool for system performance analysis in the development of the EO/IR payload.

• 한국항공운항학회지
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• 제9권2호
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• pp.63-76
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• 2001

The number of civil aviation aircraft registered in Korea has continuously increased. Accordingly the accidents accompanying loss of human or economic resources occurred repeatedly. But the analysis of flight data recorded in FDR was not done by ourselves in the accident investigation because of lack of analysis technology. Therefore, this study is performed to secure the safety of civil aviation by establishing systematic analysis ability of Flight Data Recorder. Through this study, download flight data to personal computer, editing interface file to convert from binary data to engineering data, three dimensional graphical analysis and numerical analysis are performed. For the analysis, the flight of B747-400 model aircraft between Narita(Japan) and Gimpo(Korea) was selected.

• 한국항공운항학회지
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• 제10권1호
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• pp.45-56
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• 2002

This study is performed to analyze the turbulence effect by the analysis of the parameters related with flight data of FDR(Flight Data Recorder). In the analysis, the SSFDR(Solid State Flight Data Recorder) flight data of B747-400 and B767-300 model aircraft was selected. Through this study, we verified that turbulence interfere with flight safety because it is modifiable to flight situation and condition of aircraft.

• 한국항공운항학회지
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• 제11권1호
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• pp.67-80
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• 2003

This study is performed to secure the safety of civil aviation by establishing systematic analysis ability of Flight Data Recorder. Through this study, downloading SSFDR(Solid State Flight Data Recorder) to personal computer, editing interface file, flight data numerical analysis and regulations relayed to the aircraft with carry diversion into execution are performed. In the analysis, the flight data of B747-400 model aircraft between Jeju(RKPC) and Gimpo(RKSS) was selected.

• International Journal of Aeronautical and Space Sciences
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• 제16권3호
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• pp.425-436
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• 2015

This paper presents the procedures used for estimating the stability and control derivatives of a general aviation canard aircraft from flight data. The maximum likelihood estimation method which accounts for both process and measurement noise was used for the flight data analysis of a four seat canard aircraft, the Firefly. Without relying on the parameter estimation method, several aerodynamic derivatives were obtained by analyzing the steady state flight data. A wind tunnel test, a flight test of a 1/4 scaled remotely controlled model aircraft, and the prediction of aerodynamic coefficients using the USAF Stability and Control Digital Data Compendium (DATCOM), Advanced Aircraft Analysis (AAA), and Computer Fluid Dynamics (CFD) were performed during the development phase of the Firefly and the results were compared with flight determined derivatives of a full scaled flight prototype. A correlation between the results from each method could be used for the design of the canard aircraft as well as for building the aerodynamic database.

• 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.