• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2013년도 추계학술대회
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• pp.163-164
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• 2013

양방향차도선(CAR-FERRY)은 육지와 도서, 도서와 도서 간을 연결하는 교통수단 기능과 지속적인 해양관광객의 수요증가에 따른 해양관광 연계 연안여객 운송수단 역할을 하고 있다. 이에 따른 양방향 차도선은 이용의 편리성이 증대 되고 접안으로 인한 해양 사고를 줄일 수 있다. 양방향차도선은 등흘수(even) 상태로 프로펠러가 양쪽에 있기 때문에 프로펠러가 소직경 저회전으로 인하여 전진 운항 시에 반력에 의한 축계 및 프로펠러 파손 등이 발생할 수 있다. 이에 따른 엔진 출력, 선형, 비틀림 진동 등에 따른 감속기, 탄성커플링 선정, 횡진동 및 축계정렬(Shaft alignment)을 고려한 축계설계(베어링 수량, 폭, 간격)를 하여 선체의 추진축 1차 지지부의 구조에 대한 건전성을 평가하였다.

• 천문학회보
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• 제42권2호
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• pp.58.1-58.1
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• 2017

The NISS (Near-infrared Imaging Spectrometer for Star formation history) is the near-infrared spectro-photometric instrument optimized to the first Next Generation of small satellite (NEXTSat-1). The off-axis optics was developed to cover a wide field of view with 2 deg. ${\times}$ 2 deg. as well as a wide wavelength range from 0.95 to $2.5{\mu}m$. Considering the simple alignment scheme, afocal system was adapted in the optical components. The mechanical structures were tested under the space environment. We have obtained the accurate calibration data using our test facilities under the operational condition. After the final integration of flight model into the satellite, the communication with the satellite and the functional test were passed. The NISS will be launched in early 2018. During around 2-year operation, the spectro-photometric survey covering more than 100 square degree will be performed. To achieve the major scientific objectives for the study of the cosmic star formation in local and distant universe, the main observational targets will be nearby galaxies, galaxy clusters, star-forming regions and low background regions. Here, we report the final performance of the flight model of the NISS.

• 천문학회지
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• 제51권2호
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• pp.27-36
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• 2018

In a solar coronagraph, the most important component is an occulter to block the direct light from the disk of the sun. Because the intensity of the solar outer corona is $10^{-6}$ to $10^{-10}$ times of that of the solar disk ($I_{\odot}$), it is necessary to minimize scattering at the optical elements and diffraction at the occulter. Using a Fourier optic simulation and a stray light test, we investigated the performance of a compact coronagraph that uses an external truncated-cone occulter without an internal occulter and Lyot stop. In the simulation, the diffracted light was minimized to the order of $7.6{\times}10^{-10}I_{\odot}$ when the cone angle ${\theta}_c$ was about $0.39^{\circ}$. The performance of the cone occulter was then tested by experiment. The level of the diffracted light reached the order of $6{\times}10^{-9}I_{\odot}$ at ${\theta}_c=0.40^{\circ}$. This is sufficient to observe the outer corona without additional optical elements such as a Lyot stop or inner occulter. We also found the manufacturing tolerance of the cone angle to be $0.05^{\circ}$, the lateral alignment tolerance was $45{\mu}m$, and the angular alignment tolerance was $0.043^{\circ}$. Our results suggest that the physical size of coronagraphs can be shortened significantly by using a cone occulter.

• 제어로봇시스템학회논문지
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• 제11권8호
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• pp.726-732
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• 2005

This paper proposes an autolanding guidance and control algorithm with the lateral guidance law. This algorithm is basically formulated and designed in feedback linearization based on singular perturbation. Main features of this algorithm are two facts. One of those is that when a certain situation happens that airplane must realign to the runway suddenly assigned due to unexpected environment change around the landing site, the heading guidance in this algorithm is very valuable, and the other is the fact that the inner loop control of this algorithm is able to be designed directly based on the Handling Quality Requirements that most flight control systems must be satisfied with. To illustrate the potential of this algorithm, 6-DOF nonlinear simulation based on the nonlinear airplane model shown in Ref.[11] is carried out. The simulation results showed that the altitude response to the given landing trajectory is accurate, and the airplane heading alignment to the assigned runway from the lateral deviation is successful. It is noted that this algorithm is also applicable to unmanned aerial vehicle, which can be retrieved in autolanding technique, where the runway far retrieving the vehicle is in any direction for example at war field.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.237-240
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• 2003

Gas turbines are extensively used in flight propulsion, electrical power generation, and other industrial applications. During its life span, a turbine blade is taken out periodically for repair and maintenance. This includes re-coating the blade surface and re-drilling the cooling holes/channels. A successful laser re-drilling requires the measurement of a hole within the accuracy of ${\pm}0.15mm$ in position and ${\pm}3^{\circ}$ in orientation. Detection of gas turbine blade/vane cooling hole position and orientation thus becomes a very important step for the vane/blade repair process. The industry is in urgent need of an automated system to fulfill the above task. This paper proposes approaches and algorithms to detect the cooling hole position and orientation by using a vision system mounted on a robot arm. The channel orientation is determined based on the alignment of the vision system with the channel axis. The opening position of the channel is the intersection between the channel axis and the surface around the channel opening. Experimental results have indicated that the concept of cooling hole identification is feasible. It has been shown that the reproducible detection of cooling channel position is with +/- 0.15mm accuracy and cooling channel orientation is with +/$-\;3^{\circ}$ with the current test conditions. Average processing time to search and identify channel position and orientation is less than 1 minute.

• 제어로봇시스템학회논문지
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• 제12권2호
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• pp.93-100
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• 2006

In this paper, a new-type Extended Kalman Filter (EKF) is proposed as a robust nonlinear filter for a stochastic nonlinear system. The original EKF is widely used for various nonlinear system applications. But it is fragile to its estimation errors because they give rise to linearization errors that affect the system mode1 as the modeling errors. The linearization errors are nonlinear functions of the estimation errors therefore it is very difficult to obtain the accurate error covariance of the EKF using the linear form. The inaccurately estimated error covariance hinders the EKF from being a sub-optimal estimator. The proposed filter tries to obtain the upper bound of the error covariance tolerating the uncertainty of the error covariance instead of trying to obtain the accurate one. It treats the linearization errors as uncertain modeling errors that can be handled by the robust linear filtering. In order to be more robust to the estimation errors than the original EKF, the proposed filter minimizes the upper bound like the robust linear filter that is applied to the linear model with uncertainty. The in-flight alignment problem of the inertial navigation system with GPS position measurements is a good example that the proposed robust filter is applicable to. The simulation results show the efficiency of the proposed filter in the robustness to initial estimation errors of the filter.

• 전자공학회논문지
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• 제54권7호
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• pp.81-89
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• 2017

요동이 존재하는 환경에서, 요동 측정 오차에 의한 성능 저하를 극복하기 위한 신호처리 방식의 자동초점(Autofocus, AF) 기법의 적용은 필수적이다. 본 논문에서는 스퀸트 모드에서 획득한 합성 개구면 레이다 데이터에 역투영 알고리즘(back-projection algorithm, BPA)으로 영상을 형성하고, AF를 효과적으로 적용하기 위한 방식을 연구하였다. 자동 초점 기법의 효과적인 적용을 위해 BPA 영상을 회전한 상태로 형성하는 방식을 제안하며, 이때 필요한 후처리 도플러 위치 정렬 함수를 유도하였으며, 비행시험을 통해 획득한 SAR(Synthetic Aperture Radar, SAR) 원시 데이터에 적용하여 성능 개선을 확인함으로써, 실 데이터에서도 유효한 방식임을 확인하였다.

• 한국항공우주학회지
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• 제40권11호
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• pp.997-1003
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• 2012

GNSS와 ARS는 저가의 무인 항공기를 위한 보편적인 센서로, 오차가 크며 방위각을 독립적으로 알아낼 수 없다는 단점이 있다. 또한 GNSS/INS는 초기정렬 과정과 직선비행 중에 IMU의 오차를 충분히 보상하지 못한다. 자장계는 방위각을 얻는데 효과적으로 활용되는데, 소형의 헬리콥터에 사용되는 전기모터는 정확한 방위각 산출을 방해한다. 이 논문에서는 자장계를 보상하는 방법을 제안하였으며, 비행시험으로 검증하였다. 또한 시뮬레이션 결과는 GNSS/INS에 추가된 자장계가 관측성과 정확도를 높이는 데 효과적임을 보여준다.