• 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 KIEE Conference
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• 2008.04a
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• pp.193-194
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• 2008

This paper defines the electrical interfaces and limited items to integrate Ka-band communication payload on the satellite system, which includes the detailed interfaces such as bus voltage and data bus according to the related COMS requirements. And the BUS Electrical Interface Simulator introduces to use during the course of validating and accepting between the KA-Band payload and their EGSE. These interface design results are fully validated through the testing with the BEIS and is compliant with the satellite interface control interface requirements.

• Proceedings of the KIEE Conference
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• 2002.07b
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• pp.1061-1063
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• 2002

In this paper, the characteristics of the pyro unit applied to rocket release device in KSR-Ill are analyzed by experimental results, which are the current and voltage waveforms of the battery used as energy source. The precision design approach of the rocket release device can be achieved since the behavior and the required energy of the pyro are identified through the results.

• Journal of Digital Convergence
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• v.12 no.8
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• pp.243-248
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• 2014

IPSec provides two services that are authentication header and Encapsulating Security Payload(ESP). In this research work, security issues on the Internet and the basic concept of IPSec are described. Security issues on the Internet are presented and proposed a possible solution for DDoS attack using IPSec. Therefore, this research will be able to contribute for building secure communication against DDoS attack.

• Journal of the Korean Institute of Telematics and Electronics S
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• v.35S no.2
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• pp.40-49
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• 1998

In this paper, we propose an efficient per-Trunk interworking mechanism between PSTN and ATM network assuming the situation ATM network interworks with PSTN during the evolution period. The proposed mechanism improves the cell payload utilization by mapping only the active charnnels of PSTN frame into ATM cell payload. Also, we propose the frame recovery mechanism to guarantee the frame sequence integrity. The proposed mechanism is compared with other possible ones in terms of cell payload utilization, cell packetization delay. We present the implementation structure of the interworking unit. the correctness of the mechanism and the feasibility of the implementation are verifid through the CAD simulation.

• Journal of computational fluids engineering
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• v.12 no.3
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• pp.62-68
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• 2007

A conceptual thermal design is performed for the optical payload system of a geostationary satellite. The optical payload considered in this paper is GOCI(Geostationary Ocean Color Imager) of COMS of Korea. The radiative thermal control system is employed in order to expect a small thermal gradient in the telescope structure of GOCl. Two design margins are applied to the dedicated radiator dimensioning, and three kinds of configuration to the heater power sizing. A Monte-Carlo ray tracing method and a network analysis method are utilized to calculate radiative couplings and thermal responses respectively. At the level of conceptual design, sizing thresholds are presented for the radiator and heater on the purpose of determining the mass and power budget of the spacecraft.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.1013_1014
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• 2009

In this paper, the electrical interfaces used in between COMS satellite bus and Ka-band communication payload are analyzed to verify the robustness of data bus. The purpose of the serial data bus of satellite is to allow serial data transfer between one bus controller or source equipment to several user terminals or slave equipments. A serial data bus in COMS satellite is mainly used for Channel Amplifier and Digital Control Unit of Ka-band Payload.

• Journal of Astronomy and Space Sciences
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• v.16 no.2
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• pp.131-138
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• 1999

We present the results of a model calculation of the stellar distribution in a UV and centered at 2175$\AA$ corresponding to the well-known bump in the interstellar extinction curve. The stellar distribution model used here is based on the Bahcall-Soneira galaxy model (1980). The source code for model calculation was designed by Brosch (1991) and modified to investigate various designing factors for UV satellite payload. The model predicts UV stellar densities in different sky directions, and its results are compared with the TD-1 star counts for a number of sky regions. From this study, we can determine the field of view, size of optics, angular resolution, and number of stars in one orbit. There will provide the basic constrains in designing a satellite payload for UV observations.

• 제어로봇시스템학회:학술대회논문집
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• 2005.06a
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• pp.1729-1734
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• 2005

The use of gantry crane systems for transporting payload is very common in industrial application. However, moving the payload using the crane is not an easy task especially when strict specifications on the swing angle and on the transfer time need to be satisfied. To overcome this problem, this paper describes development of an intelligent gantry crane system based on the mechatronic design. A lab-scale gantry crane is designed and then its intelligent controllers are developed. Fuzzy logic controllers are adopted, designed and implemented for controlling payload position as well as the swing angle of the gantry crane. The performance of the intelligent gantry crane system is evaluated on a hardware-in-the-loop simulation (HILS) environment. Moreover robustness of the proposed system is also evaluated. The result shows that the intelligent gantry crane system designed based on the mechatronic design approach has better performance compared with the automatic gantry crane system controlled by classical PID controllers. Moreover simulation result shows that the intelligent gantry crane system is more robust to parameter variation than the automatic gantry crane system.

• The Bulletin of The Korean Astronomical Society
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• v.42 no.2
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• pp.89.2-89.2
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• 2017

Korea Pathfinder Lunar Orbiter (KPLO) is a first Korean Lunar exploration mission. KPLO is equipped with four payloads in Korea and one payload in United States. KMAG is one of Korean payloads to measure the Moon's magnetic field. Moon has a no dipole magnetic field such as earth's global magnetic field. But there are many curious crustal magnetic anomalies. these features still do not well understood. This is a main scientific objective of KMAG payload and the study of space environment around moon is a second objective. KMAG has three magnetometers which are mounted in the edge of the 1.2 meter boom. This paper shows a KMAG's requirements, instrument description, and a preliminary function test results.