• 천문학회보
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• 제44권2호
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• pp.47.1-47.1
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• 2019

We report the design and vibration analysis for the optomechanical structures of Linear Astigmatism Free - Three Mirror System (LAF-TMS). LAF-TMS is the linear astigmatism free off-axis wide-field telescope with D = 150 mm, F/3.3, and FOV = 5.51° × 4.13°. The whole structure consists of four optomechanical modules. It can accurately mount mirrors and also can survive from vibration environments. The Mass Acceleration Curve (MAC) is adapted to the quasi-static analysis. Modal, harmonic, and random vibration analysis have been performed under the qualification level of the launch system. We evaluate the final results in terms of von Mises stress and Margin of Safety (MoS).

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2008년도 한국우주과학회보 제17권2호
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• pp.37.1-37.1
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• 2008

Space Science and Technology Laboratory at Kyung Hee University developed an 80cm Nasmyth telescope with the joint work of Space & Astronomy, Inc. It was set up at Muju county public astronomical observatory in Jeonlabuk-Do. Nasmyth focus system was selected for the telescope to use two focal points by a rotatable tertiary mirror. Focal ratios of the telescope are f10, f5 respectively. Support of the main mirror is made with Lasalle-system. This system uses 24-points in the back side of the mirror that are all resting on small counter-weights and side support is 10-points Boll link Flexible type with 2 Lasalle type. The mount is wheel & disk type Alt-Azimuth design using DC-servo motors. External high accuracy encoder has 47,600 sine-waves/rot. These encoders are used to make real-time corrections on all gearing errors.

• 한국광학회:학술대회논문집
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• 한국광학회 2007년도 동계학술발표회 논문집
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• pp.305-306
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• 2007

• Journal of Astronomy and Space Sciences
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• 제29권3호
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• pp.321-328
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• 2012

We have designed a 30 cm cryogenic space infrared telescope for astronomical observation. The telescope is designed to observe in the wavelength range of 0.5~2.1 ${\mu}m$, when it is cooled down to 77 K. The result of the preliminary design of the support structure and support method of the mirror of a 30 cm cryogenic space infrared telescope is shown in this paper. As a Cassegrain prescription, the optical system of a 30 cm cryogenic space infrared telescope has a focal ratio of f/3.1 with a 300 mm primary mirror (M-1) and 113 mm secondary mirror (M-2). The material of the whole structure including mirrors is aluminum alloy (Al6061-T6). Flexures that can withstand random vibration were designed, and it was validated through opto-mechanical analysis that both primary and secondary mirrors, which are assembled in the support structure, meet the requirement of root mean square wavefront error < ${\lambda}/8$ for all gravity direction. Additionally, when the M-1 and flexures are assembled by bolts, the effect of thermal stress occurring from a stainless steel bolt when cooled and bolt torque on the M-1 was analyzed.

• 인터넷정보학회논문지
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• 제8권5호
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• pp.117-123
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• 2007

전방위 렌즈(Catadioptric mirror)는 전방위 감시를 위해 널리 사용되고 있다. 대부분의 전방위 렌즈에서의 단점은 전방위 렌즈를 통하여 획득한 영상의 해상도가 위치에 따라 일정하지 않다는데 있다. 본 논문에서 사용한 등거리 전방위 렌즈는 이러한 문제를 해결할 수 있도록 설계된 렌즈이다. 실제 등거리 전방위 렌즈를 통한 거리 계산 시 오류의 원인으로는 카메라 영상 센서와 전방위 렌즈와의 축의 어긋남, 설계 시 가정한 focal length의 변화 등을 들 수 있는데 이 중 focal length의 변화는 기구의 정확한 제작으로 해결할 수 없는 문제이다. 본 논문에서는 이러한 focal length의 변화에 대처하기 위하여 focal length를 수정하는 방법을 제안한다. 영상 정합을 통해 임의로 선정된 두 개의 object points에 대한 반대편 스테레오 영상에서 대응점을 찾은 후 이들 화소의 원점에서의 거리를 사용하여 경계에 해당하는 화소의 위치를 찾는다. 이렇게 측정된 경계의 위치가 미리 계산된 경계화소의 위치와 다를 경우 제안한 방법으로 focal length의 값을 수정한다. 제안한 방법은 매우 간단한 계산만으로 기존의 반복적 연산을 통해 수행한 focal length 수정 방법과 유사한 성능을 보인다.

• Journal of Astronomy and Space Sciences
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• 제27권2호
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• pp.153-160
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• 2010

We modified the optical system of 500 mm wide-field telescope of which point spread function showed an irregularity. The telescope has been operated for Near Earth Space Survey (NESS) located at Siding Spring Observatory (SSO) in Australia, and the optical system was brought back to Korea in January 2008. After performing a numerical simulation with the tested value of surface figure error of the primary mirror using optical design program, we found that the surface figure error of the mirror should be fabricated less than root mean square (RMS) $\lambda$/10 in order to obtain a stellar full width at half maximum (FWHM) below $28\;{\mu}m$. However, we started to figure the mirror for the target value of RMS $\lambda$/20, because system surface figure error would be increased by the error induced by the optical axis adjustment, mirror cell installation, and others. The radius of curvature of the primary mirror was 1,946 mm after the correction. Its measured surface figure error was less than RMS $\lambda$/20 on the table of polishing machine, and RMS $\lambda$/15 after installation in the primary mirror cell. A test observation performed at Daeduk Observatory at Korea Astronomy and Space Science Institute by utilizing the exiting mount, and resulted in $39.8\;{\mu}m$ of stellar FWHM. It was larger than the value from numerical simulation, and showed wing-shaped stellar image. It turned out that the measured-curvature of the secondary mirror, 1,820 mm, was not the same as the designed one, 1,795.977 mm. We fabricated the secondary mirror to the designed value, and finally obtained a stellar FWHM of $27\;{\mu}m$ after re-installation of the optical system into SSO NESS Observatory in Australia.

• 대한기계학회논문집A
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• 제32권8호
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• pp.693-700
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• 2008

The primary mirror system in a satellite camera is an opto-mechanically coupled system for a reason that optical and mechanical behaviors are intricately interactive. In order to enhance the opto-mechanical performance of the primary mirror system, opto-mechanical behaviors should be thoroughly investigated by using various analysis procedures such as elastic, thermo-elastic, optical and eigenvalue analysis. In this paper, optimal design of the bipod flexure mounts for high opto-mechanical performance is performed. Optomechanical performances considered in this paper are RMS wavefront error under the gravity and thermal loading conditions and 1st natural frequency of the mirror system. The procedures of the flexure mounts design based on design of experiments and statistics is as follows. The experiments for opto-mechanical analysis are constructed based on the tables of orthogonal arrays and analysis of each experiment is carried out. In order to deal with the multiple opto-mechanical properties, MADM (Multiple-attribute decision making) is employed. From the analysis results, the critical design variables of the flexure mounts which have dominant influences on opto-mechanical performance are determined through analysis of variance and F-test. The regression model in terms of the critical design variables is constructed based on the response surfaceanalysis. Then the critical design variables are optimized from the regression model by using SQP algorithm. Opto-mechanical performance of the optimal bipod flexure mounts is verified through analysis.

• 천문학회보
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• 제41권2호
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• pp.66.3-67
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• 2016

The Giant Magellan Telescope (GMT) will feature two interchangeable Gregorian secondary mirrors, an adaptive secondary mirror (ASM) and a fast-steering secondary mirror (FSM). The FSM has an effective diameter of 3.2 m and built as seven 1.1 m diameter circular segments, which are conjugated 1:1 to the seven 8.4m segments of the primary. Each FSM segment contains a tip-tilt capability for fine co-alignment of the telescope subapertures and fast guiding to attenuate telescope wind shake and mount control jitter. This tip-tilt capability thus enhances performance of the telescope in the seeing limited observation mode. As the first stage of the FSM development, KASI conducted a Phase 0 study to develop a program plan detailing the design and manufacturing process for the seven FSM segments. The GMTO-KASI team matured this plan via an internal review in May 2016 and the revised plan was further assessed by an external review in June 2016. In this poster, we present the technical aspects of the FSM development plan.

• 천문학논총
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• 제30권3호
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• pp.833-833
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• 2015

• 한국광학회지
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• 제22권6호
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• pp.262-268
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• 2011

한국천문연구원이 개발한 다목적적외선영상시스템(Multi-purpose IR Imaging System, MIRIS)은 과학기술위성 3호(STSAT-3)의 주탑재체이다. 지구관측카메라(Earth Observation Camera, EOC)는 MIRIS를 구성하는 두 개의 적외선 카메라 중에 하나로, 지구의 $3{\sim}5{\mu}m$ 파장대의 적외선을 관측하기 위한 카메라이다. EOC의 광학계는 카세그레인 방식으로써 구경이 100 mm이고, 주경과 부경은 모두 비구면 반사경이다. EOC 주경의 플렉서는 링 타입으로써 발사환경에서 주경이 겪을 수 있는 충격과 진동을 견디도록 예압을 가하며 주경을 지지한다. 이는 마치 리테이너로 렌즈를 지지하는 것과 같은 메커니즘으로 주경을 지지하기 위한 시도이다. 광기계 해석을 통해 EOC 주경이 효과적으로 지지되고 있음을 확인했다.