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박욱제,김종걸 대한안전경영과학회 2006 대한안전경영과학회 학술대회논문집 Vol.2006 No.11
제품을 로트(lot)단위로 구분하고 로트에서 취한 샘플을 검사하여 얻은 품질 특성의 값을 이용해서 로트의 합격여부를 판정하는 것을 샘플링검사(sampling inspection)라 하고, 검사하는 품질특성이 제품의 수명 특성치인 경우에 이를 신뢰성 샘플링 검사(reliability sampling inspection)라 한다. 그 중 벌크재료에 대한 샘플링 검사방식을 알아 보도록한다.
박욱제,김종걸 대한안전경영과학회 2006 대한안전경영과학회 학술대회논문집 Vol.2006 No.1
제품을 로트(lot)단위로 구분하고 로트에서 취한 샘플을 검사하여 얻은 품질 특성의 값을 이용해서 로트의 합격여부를 판정하는 것을 샘플링검사(sampling inspection)라 하고, 검사하는 품질특성이 제품의 수명 특성치인 경우에 이를 신뢰성 샘플링 검사(reliability sampling inspection)라 한다. 그 중 벌크재료에 대한 샘플링 검사방식을 알아 보도록한다.
Fault detection and isolation of DURUMI-II using similarity measure
박욱제,Sang H. Lee,송정일 대한기계학회 2009 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.23 No.2
This paper describes the flight test method for studying the primary control surface stuck condition and the combination stuck of the primary control. An aircraft must show controllability and trimmability under post-failure conditions. An aircraft is successfully tested under various fault conditions. It is recognized that a control surface fault is detected by monitoring the value of the coefficients related to the control surface deviation. The control surface stuck position is determined by comparing the trim value with the reference value. To detect and isolate the fault, an analysis that employs the real-time parameter estimation method is used. If the flight control system is reconfigured using online estimates of aircraft parameters from a real-time parameter estimation scheme, the reliability increases without the addition of sensors or additional cost.
論文(논문) : 무게중심 변화에 따른 자유날개 동체꺾임형 항공기의 조종성 해석
박욱제 ( Wook Je Park ) 한국항공운항학회 2011 한국항공운항학회지 Vol.19 No.4
The free-wing tilt-body aircraft is researched in the flight performance characteristics for center of gravity (CG) change. All of speed, body tilt angle and center of gravity change are simulated to determine the flight envelope by a non-linear 3-DOF mathematical model. In flight, this aircraft configuration changes by the tiltable empennage. Then, flight dynamics distinguishes from those of a conventional fixed-wing aircraft. Though flight performance and trimmability are studied by CG change, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics by CG change that distinguishes free-wing tilt-body aircraft from the conventional aircraft.
박욱제,황명신,송용규 한국항공대학교 1998 論文集 Vol.36 No.-
To obtain aircraft dynamic parameters, various estimation methods such as Maximum Likelihood, Linear Regression are applied. In this paper we adopt the extended Kalman filter(EKF) to estimate the stability and control derivatives in aircraft dynamic models from flight test data. The extended Kalman filter is applied to nonlinear augmented system assuming that unknown parameters are additional states. In this work, the results of the extended Kalman filter are compared with those of the wind tunnel test and Modified Maximum Likelihood Estimation(MMLE) using ChangGong-91 aircraft flight test data.
論文(논문) : 유사측도를 이용한 무인기의 고장진단 및 검출
박욱제 ( Wook Je Park ),이상혁 ( Sang Hyuk Lee ) 한국항공운항학회 2011 한국항공운항학회지 Vol.19 No.2
It is recognized that the control surface fault is detected by monitoring the value of the coefficients due to the control surface deviation. It is found out the control surface stuck position by comparing the trim value with the reference value. To detect and isolate the fault, two mixed methods apply to the real-time parameter estimation and similarity measure. If the scatter of aerodynamic coefficients for the fault and normal are closing nearly, fault decision is difficult. Applying similarity measure to decide for fault or not, it makes a clear and easy distinction between fault and normal. Low power processor is applied to the real-time parameter estimator and computation of similarity measure.
論文(논문) : 자유날개 동체꺾임형 항공기의 조종성 해석
박욱제 ( Wook Je Park ) 한국항공운항학회 2011 한국항공운항학회지 Vol.19 No.1
The free-wing tilt-body aircraft is researched in the flight performance characteristics such as short take-off and landing capability, and reduced sensitivity to gust and center of gravity (CG) change. Due to the main wing separating from the fuselage, the high tiltable empennage, and the stub-wing strongly influencing from the propeller wake, the resulting vehicle aerodynamics and flight dynamics are quite different from those of a conventional fixed-wing aircraft. Using the governing flight dynamics model was studied previously, all of speed and body tilt angle is simulated to determine the flight envelope by a non-linear 3-DOF flight simulation analysis. Though flight performance and trimmability are studied, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics that distinguishes free-wing tilt-body aircraft from the conventional aircraft.