• The Transactions of The Korean Institute of Electrical Engineers
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• v.57 no.7
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• pp.1285-1289
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• 2008

In this paper, we design COMS system bus that the 1553 Data Bus is able to link all the units of the satellite managed by the SCU using one Prime Data Bus and on Redundant Data Bus. Also we analyze MIL-STD-1553B bus load and relevant exchange memory budgets in system bus of the COMS satellite. This data is used in the satellite mission and software design by system engineer.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.11
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• pp.47-53
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• 2006

The power losses due to modulation index for multi-modulation scheme were analyzed under various transmission mode of satellite control and the necessary satellite link margin for transmission mode were proposed in this paper On the basis of the analyses for interference between the transmission signals and threshold of satellite control signal receiver, the optimal subcarrier signals were proposed for satellite range measurement methods, respectively. The subcarrier signal of 12 kHz or 14 kHz is proper for telecommand using the ESA method, and 16 kHz for telecommand signal using the GSTDN method. On the other hand, the telemetry subcarrier of 65.536 kHz is a proper in the viewpoint of receiver threshold value.

• ETRI Journal
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• v.27 no.2
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• pp.140-152
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• 2005

In this paper, we present design features, implementation, and validation of a satellite simulator subsystem for the Korea Multi-Purpose Satellite-2 (KOMPSAT-2). The satellite simulator subsystem is implemented on a personal computer to minimize costs and trouble on embedding onboard flight software into the simulator. An object-oriented design methodology is employed to maximize software reusability. Also, instead of a high-cost commercial database, XML is used for the manipulation of spacecraft characteristics data, telecommand, telemetry, and simulation data. The KOMPSAT-2 satellite simulator subsystem is validated by various simulations for autonomous onboard launch and early orbit phase operations, anomaly operation, and science fine mode operation. It is also officially verified by successfully passing various tests such as the satellite simulator subsystem test, mission control element system integration test, interface test, site installation test, and acceptance test.

• Journal of electromagnetic engineering and science
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• v.9 no.4
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• pp.223-228
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• 2009

In this paper, a quadrafilar antenna is designed to have a lower profile as an essential part of the size reduction technique and lower back radiation(i.e. higher forward radiation) for the S-band telemetry/telecommand(TM/TC) function of a communication satellite. Particularly, to meet the challenging requirements on the higher isolation between the TM/TC antennas and simultaneously a smaller size, the lowest back radiation and lowest cross-polarization, the optimal physical dimensions of the quadrafilar antenna are found by using the Genetic Algorithm(GA). To prove the validity of the proposed antenna design, its 3D electromagnetic analysis and measured results are compared, showing good agreement.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.58 no.12
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• pp.2468-2473
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• 2009

In this paper, a quadrafilar antenna is designed to have a lower profile as an essential part of the size reduction technique and lower backradiation(namely, higher forward radiation) for the S-band telemetry/telecommand(TM/TC) function of a communication satellite. Particularly, to meet the challenging requirements on the higher isolation between the TM/TC antennas and simultaneously a smaller size, the lowest backradiation and lowest cross-polarization, the optimal physical dimensions of the quadrafilar antenna are found by using the Genetic Algorithm(GA). To prove the validity of the proposed antenna design, its 3D electromagnetic analysis and measured results are compared to show good agreement. Using this antenna as the elements, an array antenna is made to have directivity.

• Proceedings of the KIEE Conference
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• 2005.07b
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• pp.1438-1440
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• 2005

A power control and distribution unit(PCDU) plays roles of protection of battery against overcharge by active control of solar array generated power, distribution of unregulated electrical power via controlled outlets to bus and instrument units, distribution of regulated electrical power to selected bus and instrument units, and provision of status monitoring and telecommand interface allowing the system and ground operate the power system, evaluate its performance and initiate appropriate countermeasures in case of abnormal conditions. In this work, we perform the preliminary design of a PCDU scheme for the small LEO Satellite applications. The main constitutes of the PCDU are the battery interface module, the auxiliary supply modules, solar array regulators with maximum power point tracking(MPPT) technology, heater power distribution modules, internal converter modules for regulated bus voltage generation. and instrument power distribution modules.

• Current Industrial and Technological Trends in Aerospace
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• v.8 no.1
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• pp.112-117
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• 2010

In this paper..We are introducing the World Radiocommunication Conference (WRC 2007) decided upon new additional frequency allocations for Aeronautical Mobile Telemetry and International Telecommunication Union (ITU) that is leading United Nations agency for information and communication technology issues, World Radiocommunication Conference (WRC) that revise the Radio Regulations, the international treaty governing the use of the radio-frequency spectrum. We are describing the international trends and korea frequency allocation tables revision after it has allocated to the aeronautical mobile telemetry frequency spectrum.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.80-89
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• 2010

Transponder is the significant equipment for the telemetry and telecommand operation between the ground station and the satellite. Recently, various transponder technology like Compact Standard Transponder(CST), Small User Transponder(SUT) for data relay satellite, Dual Mode TT&C Transponder(DMT) for large user, and Deep Space Transponder(DST) for deep space mission have been developed according to the communication method and user requirements. Especially, the transponder based on the digital technology comes into the spotlight in the satellite communication field. This paper describes the various analog transponder technology and the state-of-art digital transponder technology grafted onto the existing analog transponder technology.

• Proceedings of the Korean Institute of IIIuminating and Electrical Installation Engineers Conference
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• 2005.05a
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• pp.283-287
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• 2005

In this paper, one general approach is proposed for the design of power system that can be applicable for next generation LEO satellite application. The power system consists of solar panels, battery, and power control and distribution unit(PCDU). The PCDU contains solar array modules, battery interface modules, low-voltage power distribution modules, high-voltage distribution modules, heater power distribution modules, on-board computer interface modules, and internal DC/DC converter modules. The PCDU plays roles of protection of battery against overcharge by active control of solar array generated power, distribution of unregulated electrical power via controlled outlets to bus and instrument units, distribution of regulated electrical power to selected bus and instrument units, and provision of status monitoring and telecommand interface allowing the system and ground operate the power system, evaluate its performance and initiate appropriate countermeasures in case of abnormal conditions. We review the functional schemes of the main constitutes of the PCDU such as the battery interface module, the auxiliary supply module, solar array regulators with maximum power point tracking(MPPT) technology, heater power distribution modules, spacecraft unit power distribution modules, and instrument power distribution module.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2017.05a
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• pp.391-393
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• 2017

Unmanned aerial vehicles(UAVs) operating in the military for various purposes are designed to transmit information collected according to the purpose to GCS(Ground Control System), and to transmit/receive the vehicle's operational control and status information using wireless communication(or datalink). Currently, the military UAV systems in operation in Korea use unique communication methods, protocols, and message structures for each system. In this paper, we analyze the TM/TC data protocol of two types of military UAV systems currently under development and propose a more efficient TM/TC message design scheme in wireless communication(or datalink) environment. And we will discuss issues to be considered for standardization of technology for ensuring interoperability with many UAVs or newly introduced UAV systems.