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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.
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.
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.
비행중 실시간 파라미터 추정기법을 이용한 커나드 비행기의 가로안정성에 관한 연구
박욱제(Wook-je Park),노양수(Yang-soo Noh),최진원(Jin-won Choi),문정호(Jung-ho Moon),황명신(Myoung-shin Hwang),성기정(Kee-jeong Seong) 한국항공우주학회 2004 韓國航空宇宙學會誌 Vol.32 No.9
본 논문은 실제의 비행시험 데이터를 이용하여 커나드 비행기 Velocity-173의 가로-방향의 조종/안정 미계수들을 추정하는 것이며, 나아가서 비행중에(In-Flight) 실시간 파라미터 추정기법을 이용한 미계수 확인 및 분석에 관한 내용이다. 본 논문에서 적용한 비행중 실시간 파라미터 추정기법의 결과는 AAA의 해석 결과와 비교하였으며 그 결과는 상당히 신뢰할 수 있고 계산시간 또한 만족스러움을 확인하였다. 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.
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.
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.
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.