• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.10
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• pp.98-103
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• 2005

The Flight Model of MAC (Medium-sized Aperture Camera), a 2.5m GSD class earth observation camera has been aligned and assembled. Topics discussed in this paper include the ground MTF performance of the MAC system, and the alignment of the focal plane assembly. MTF was measured by a knife-edge scanning technique, and a 450 mm diameter Cassegrain collimator with diffraction-limited performance was made and used for the MTF measurements. System MTF was used as the figure-of-merit to find the best focus of the focal plane assembly.

• Proceedings of the Optical Society of Korea Conference
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• 1995.06a
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• pp.53-58
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• 1995

Examples of advanced digital electro-optic imaging systems for the satellite remote sensing applications are introduced including multispectral focal plane assembly for newly proposed 1-m spatial resolution capability.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.2
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• pp.179-185
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• 2015

The main objective of thermal design for a space-borne FPA(Focal Plane Assembly) is to provide stable thermal environment during imaging operation and thus maintain the image quality. An FPA must be maintained within its operating temperature range and cooled down to its initial temperature soon enough for the next imaging operation. This paper describes the study result on performing trade-off studies for FPA thermal design by using simplified thermal node analysis about FPA preliminary design. It also describes the verification results of the study by comparing thermal analysis results and trade-off study results. According to results, we can conclude that this approach is useful for simple and quick trade-off studies without thermal analysis based on thermal math models.

• Proceedings of the KSRS Conference
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• 2005.10a
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• pp.225-228
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• 2005

Telescope structure based on Korsch type optical layout was suggested for a large aperture optical system. Korsch type optical layout is regarded as providing wide field of view and no color aberration for which high resolution space cameras greatly demand. For the suggested Korsch type telescope structure, two folding mirrors are adopted, firstly to provide for the refocusing device mounting plane on the second fold mirror assembly, secondly by double folding the light path to concisely confine focal plane assembly within the perimeter of the tube. Optical layput design and corresponding support structure design were attained.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.580-585
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• 2009

Thermal analysis and design of FPA(Focal Plane Assembly)-CU(Cooling Unit) for Earth observation camera is performed. FPA-CU is the first cooling device for a spacecraft which is designed and manufactured by its own technology in Korea. FPA-CU has a special feature, TBM(Thermal Buffer Mass) which is discriminated from typical cooling devices using heat pipes and radiator. TBM can be regarded as a thermal energy reservoir and it shows thermally transient characteristics, which make it difficult to design the size and shape of TBM. In current study, a method to determine the volume and the size of TBM is proposed and validated. The transient thermal analysis for FPA-CU for 5 operational scenarios is performed and validates the final design of FPA-CU (Radiator,TBM, Heat pipe I/F). In case of an abnormal operation of a heat pipe among three radiator heat pipes, the temperature of FPA can be increased $3{\sim}4^{\circ}C$ according to the numerical simulation.

• Current Optics and Photonics
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• v.7 no.4
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• pp.398-407
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• 2023

We explored a method to evaluate imaging performance for the optimal assembly of an endoscopic miniature lens and a sensor constituting an imaging module at the distal end of gastrointestinal endoscopy. For the assembly of the imaging module, the image sensor was precisely located at the focal plane when collimated light passed through the endoscopic lens. As another method, the distance between the lens and sensor was adjusted to obtain the highest focus index from images measured the star chart of the International Organization for Standardization (ISO) standard at various positions. We analyzed the slanted-edge modulation transfer function (MTF), corresponding depth of field, and number of line pairs for MTF 50% and 20% at each working distance within the range of 5-100 mm for imaging modules assembled in different ways. Assembly conditions of the imaging module with better MTF performance were defined for each working distance range of 5-30 mm and 30-100 mm, respectively. In addition to the MTF performance, the focus index of each assembled module was also compared. In summary, we examined the performance of imaging modules assembled with different methods within the suggested working distance and tried to establish the optimal assembly protocol.

• Proceedings of the IEEK Conference
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• 2008.06a
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• pp.1157-1158
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• 2008

This paper describes the interface designs of Optical-Camera Electronic unit with a DFPA(Detector Focal Plane Assembly) and IDHU(Image Data Handling Unit) which meet the top-level requirement of a satellite system. Especially, the designs on the image format and timing of the Header information for the correct reconstruction of the image in the Groundstation are explained in detail.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.161-167
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• 2010

CEU(Camera Electronic Unit) loaded in optical satellite for a high resolution image acquisition is composited with CC(Camera Controlloer), FPA(Focal Plane Assembly) and CEUP(CEU Power supply). EMC test and analysis results are explained in this paper. CE, CS, RE and RS test is performed in the 1st EMC test, RE, RS test which is not complied and influence considerably after shielding structure is performed in the 2nd EMC test. An effect due to the noise of CEU in the GPS/S-band receiving band is analyzed based on 2nd EMC test results. Margin more than 6dB is guaranteed when CEU is shielded.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.20-28
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• 2011

The electro-optical payload of a low-earth orbit satellite is thermally decoupled with the bus, which supports a payload for a mission operation. The payload has a cooling unit of FPA(Focal Plane Assembly) which has a thermal behavior increasing its temperature instantly during an operation in order to dissipate a waste heat into the space. The FPA cooling unit should include a radiator and heatpipes with a sufficient performance in worst hot condition, and a heater design to maintain its temperature above a minimum allowable temperature in the worst cold condition. In this paper, we analyzed the thermal requirements and the heater design constraints from the thermal analysis results for the current thermal design of the FPA cooling unit and the design elements of the better heater design were found.

• Proceedings of the KSRS Conference
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• 2004.10a
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• pp.452-455
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• 2004

MSC (Multi-Spectral Camera) system is a remote sensing instrument to obtain high resolution ground image. EOS (Electro-Optic System) for MSC mainly consists of PMA (Primary Mirror Assembly), SMA (Secondary Mirror Assembly), HSTS (High Stability Telescope Structure) and DFPA (Detector Focal Plane Assembly). High performance of EOS makes it possible for MSC system to provide high resolution and high quality ground images. Temperature of the EOS needs to be controlled to be in a specific range in order not to have any thermal distortion which can cause performance degradation. It is controlled by full redundant CPU based electronics. The validity of thermistor readings can be checked because a few thermistors are installed on each control point on EOS. Various kinds of thermal control logics are used to prevent 'Single Point Failure'. Control logic has a few set of database in order not to be corrupted by SEU (Single Event Upset). Even though the thermal control logic is working automatically, it can also be monitored and controlled by ground-station operator. In this paper, various ways of thermal control logic for EOS in MSC will be presented, which include thermal control mode and logic, redundancy design and status monitoring and reporting scheme.