• 항공우주기술
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• 제9권2호
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• pp.161-167
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• 2010

지구관측을 위한 광학위성에 탑재되는 고해상도 영상 획득을 목적으로 하는 위성카메라의 카메라전자부(CEU : Camera Electronic Unit)는 CC(Camera Controller)와 FPA(Focal Plane Assembly), CEUP(CEU Power supply)로 구성된다. 본 논문은 광학위성 탑재체(CEU)의 전자파시험결과와 이를 토대로 한 시스템 양립성 검토결과를 설명하였다. CEU의 1차 전자파시험은 전도성 방출시험, 전도성 감응시험, 복사성 방출시험 및 복사성 감응시험을 수행하였고 2차 시험에서는 1차 시험에서 규격을 만족하지 못함으로서 시스템 성능에 중요한 영향을 미칠 수 있는 복사성 방출시험과 복사성 감응시험을 차폐제를 이용하여 기구적인 차폐를 보강 후 수행하였다. 2차 시험결과에 대한 시스템 양립성은 탑재체(CEU)에서 방출하는 노이즈의 주파수성분이 위성의 GPS/S-Band 수신 성능에 미치는 영향성을 분석하였다. 기구적인 차폐보강이 전제되었을 때, 두 수신대역 내에서 발생하고 있는 노이즈 주파수성분에 대하여 6dB 이상의 마진을 갖는 것으로 나타났다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
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• pp.1121-1123
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• 2003

The CCD (Charge coupled device) detector that is used to convert the light into electronic data is very important component in satellite camera. A Linear CCD Spectral detector shall be used in the MSC (Multi-Spectral Camera, to obtain data for high-resolution images) Payload. In this paper, the design concept of the CCD detector control module in the MSC CEU (Camera electronic unit) system which will be a payload on KOMPSAT is described in terms of H/W (clock speed and accuracy).

• 대한원격탐사학회지
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• 제26권6호
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• pp.645-652
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• 2010

The performance of the payload Electro-Optical System (EOS) in satellite system is affected by various factors, such as optics design, camera electronics design, and the characteristics of the CCD (Charge Coupled Device) used, etc. Of these factors, the camera electronics design is somewhat unique in that its operational parameters can be adjusted even after the satellite launch. In this paper, the effect of video gain on the non-uniformity correction performance is addressed. And a new optimal non-uniformity correction scheme is proposed and analyzed using the data from real camera electronics unit based on a TDI (Time Delayed Integration) type of CCD. The test results show that the performance of the conventional non-uniformity correction scheme is affected significantly when the video gain is added. On the other hand, in our proposed scheme, the performance is not dependent on the video gain. The insensitivity of the non-uniformity performance on the video-gain is mainly due to the fact that the correction is performed after the dark signal is subtracted from system response.

• International Journal of Aerospace System Engineering
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• 제5권2호
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• pp.8-15
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• 2018

For small earth observation satellites, alignment between the optical components is important for precise observation. However, satellite cameras are structurally subject to misalignment in the launch environment where vibration excitations and impacts apply, and in space environments where zero gravity, vacuum, radiant heat and degassing occur. All of these variables can cause misalignment among the optical components. The misalignment among optical components results in degradation of image quality, and a re-alignment process is needed to compensate for the misalignment. This process of re-alignment between optical components is referred to as a refocusing process. In this paper, we proposed a 3 - axis focusing mechanism to perform the refocusing process. This mechanism is attached to the back of the secondary mirror and consists of three piezoelectric inertia-friction actuators to compensate the x-axis, y-axis tilt, and de-space through three-axis motion. The fabricated focus mechanism demonstrated excellent servo performance by experimenting with PD servo control.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
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• pp.453-454
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• 2003

Most research materials (data), which are used for the study of digital mapping and digital elevation model (DEM) in the field of Remote Sensing and Aerial Photogrammetry are aerial photographs and satellite images. Additionally, they are also used for National land mapping, National land management, environment management, military purposes, resource exploration and Earth surface analysis etc. Although aerial photographs have high resolution, the data, which they contain, are not used for environment exploration that requires continuous observation because of problems caused by its coastline, as well as single - spectral and long-term periodic image. In addition to this, they are difficult to interpret precisely because Satellite Images are influenced by atmospheric phenomena at the time of photographing, and have by far much lower resolution than existing aerial photographs, while they have a great practical usability because they are mulitispectral images. The PKNU 2 is an aerial photographing system that is made to compensate with the weak points of existing aerial photograph and satellite images. It is able to take pictures of very high resolution using a color digital camera with 6 million pixels and a color infrared camera, and can take perpendicular photographs because PKNU 2 system has equipment that makes the cameras stay level. Moreover, it is very cheap to take pictures by using super light aircraft as a platform. It has much higher resolution than exiting aerial photographs and satellite images because it flies at a low altitude about 800m. The PKNU 2 can obtain multispectral images of visible to near infrared band so that it is good to manage environment and to make a classified diagram of vegetation.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2005년도 창립60주년 기념 추계 학술대회
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• pp.22.1-22.1
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• 2005

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 1994년도 한국우주과학회보 제3권2호
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• pp.35-35
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• 1994

No Abstract. See Full-text

• 항공우주시스템공학회지
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• 제12권3호
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• pp.86-96
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• 2018

본 논문에서 제안한 캔위성은 2017년 캔위성 경연대회에 출전한 $HA+RC^2S$ CanSat (High Agility and Remote Control Camera System Can Satellite)이다. 주요임무는 수동진동감쇠기인 동흡진기를 사용하여 카메라를 회전시킨 직후에 발생하는 잔류진동을 감쇠하여 고품질의 영상획득이 가능한 고기동 안정화 카메라 시스템을 검증하는 것이다. 부가적으로는 지상국의 조이스틱을 사용하여 무선으로 제어되는 원격 제어 셀프카메라로 캔위성 자체의 이미지데이터를 획득하는 것이다. 본 논문에서는 임무 정의, 시스템 설계, 제작, 기능 및 성능시험, 최종 비행시험을 포함하는 $HA+RC^2S$ CanSat의 개발과정에 대해 서술하였다.

• 대기
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• 제29권1호
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• pp.61-74
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• 2019

To investigate the observational environment, sky line and skyview factor (SVF) are calculated using a digital elevation model (DEM; 10 m spatial resolution) and 3 dimensional (3D) sky image at radiation site, Gangneung-Wonju National University (GWNU). Solar radiation is calculated using GWNU solar radiation model with and without the sky line and the SVF retrieved from the 3D sky image and DEM. When compared with the maximum sky line elevation from Skyview, the result from 3D camera is higher by $3^{\circ}$ and that from DEM is lower by $7^{\circ}$. The SVF calculated from 3D camera, DEM and Skyview is 0.991, 0.998, and 0.993, respectively. When the solar path is analyzed using astronomical solar map with time, the sky line by 3D camera shield the direct solar radiation up to $14^{\circ}$ with solar altitude at winter solstice. The solar radiation is calculated with minutely, and monthly and annual accumulated using the GWNU model. During the summer and winter solstice, the GWNU radiation site is shielded from direct solar radiation by the west mountain 40 and 60 minutes before sunset, respectively. The monthly difference between plane and real surface is up to $29.18M\;m^{-2}$ with 3D camera in November, while that with DEM is $4.87M\;m^{-2}$ in January. The difference in the annual accumulated solar radiation is $208.50M\;m^{-2}$ (2.65%) and $47.96M\;m^{-2}$ (0.63%) with direct solar radiation and $30.93M\;m^{-2}$ (0.58%) and $3.84M\;m^{-2}$ (0.07%) with global solar radiation, respectively.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2006년도 Proceedings of ISRS 2006 PORSEC Volume II
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• pp.797-799
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• 2006

The Electro-optical camera subsystem as a payload of a satellite system consists of OM (optical module) and CEU(camera electronics unit), and most performances of the camera subsystem depend a lot on the CEU in which TDI CCDs(Time Delayed Integration Charge Coupled Device) take the main role of imaging by converting the light intensity into measurable voltage signal. Therefore it is required to specify and design the CEU very carefully at the early stage of development with overall specifications, design considerations, calibration definition, test methods for key performance parameters. This paper describes the overview of CEU development. It lists key requirement characteristics of CEU hardware and design considerations. It also describes what kinds of calibration are required for the CEU and defines the test and evaluation conditions in verifying requirement specifications of the CEU, which are used during acceptance test, considering the fact that CEU performance results change a lot depending on test and evaluation conditions such as operational line rate, TDI level, and light intensity level, so on.