• The Transactions of The Korean Institute of Electrical Engineers
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• v.59 no.4
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• pp.774-778
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• 2010

In this paper, the preliminary EMC analysis process between the Communication, Ocean and Meteorological Satellite (COMS) and the Geostationary Earth Orbit (GEO) launch vehicles in the frequency range is described. The considered launch vehicles are Arian Ⅴ, Sea Launch, Land Launch, Atlas III&Ⅴ, Delta IV, Proton M/breeze M, Soyuz, H II-Aa. The launch vehicle Radiated Susceptibility (RS) specifications have been compared to COMS satellite Radiated Emission (RE) limits. The COMS Radiated Emission (RE) level is determined by calculating the radiated field equal to the quadratic sum of radiated emissions of each equipment switched "ON" during launch. As a result, The RS requirements of Arian V, Atlas III&V and Delta IV lauchers are compliant with COMS RE limits. The negative margins appear between the others launch vehicle RS (Sea Launch, Land Launch, Proton M/Breeze M, Soyuz and H II-A) and COMS RE. Then, if the launchers that have negative margin were chosen by the customer, The EMC tests should be performed at satellite level in order to demonstrate the compatibility with respect to launch vehicles requirements.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.20 no.12
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• pp.1272-1278
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• 2009

The cancellation method of P/G(power/ground) plane resonances which are generated between the power plane and the ground plane in a 4-layer PCB(Printed Circuit Boards) with a via-hole for the improvement of the RE(Radiated Emission) characteristic is presented. The validity of the proposed method was confirmed from simulation and measurement of performances of signal transmission characteristic, intensities of edge-radiation and radiated emission of PCB with a via-hole.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.57 no.3
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• pp.439-445
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• 2008

In this paper, the preliminary EMC analysis process between the Communication, Ocean and Meteorological Satellite (COMS) and Geostationary Earth Orbit (GEO) launch vehicles in the frequency range [1MHz-47MHz] is described. The considered launch vehicles are arian V, sea Launch, land Launch, atlas III&V, delta IV, proton M/breeze M, soyuz, HII-A and Angara. The launch vehicle Radiated Emission (RE) specifications have been compared to COMS satellite Radiated Susceptibility (RS) limits. The COMS RS limits are the RS qualification levels of COMS units during launch. As a result, The radiated emission levels of arian V, sea launch, atlas III&V, delta IV, proton M/breeze M, HII-A and angara are compliant with COMS RS limits. The negative margins appear between land launch or soyuz launch vehicle RE and COMS RS. Then, if the land launch or soyuz is chosen by the customer, The tests should be performed at satellite level in order to demonstrate the compatibility with respect to launch vehicles specifications.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.1574_1575
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• 2009

This paper investigates the reduction of RE(Radiated Emission) noise in a high power LED module circuit using PWM(Pulse Width Module) switching controller circuit. Poorly designed LED lighting module can experience the RE and CE(Conducted Emission) noise problem. This paper propose the reduction of noise source and improvement of EMI filter design in a high power LED lighting module. The experimental and simulation results showed that reduce the RE noise level effectively.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.33-40
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• 2009

In this paper, the preliminary EMC analysis process between the Communication, Ocean and Meteorological Satellite (COMS) and Geostationary Earth Orbit (GEO) launch vehicles in the frequency range [1MHz-47MHz] is described. The launch vehicle Radiated Emission (RE) specifications have been compared to COMS satellite Radiated Susceptibility (RS) limits. The COMS RS limits are the RS qualification levels of COMS units during launch. The negative margins appear between land launch or soyuz launch vehicle RE and COMS RS. Then, if the land launch or soyuz is chosen by the customer, The tests should be performed at satellite level in order to demonstrate the compatibility with respect to launch vehicles specifications.

• Journal of electromagnetic engineering and science
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• v.7 no.1
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• pp.7-11
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• 2007

PCB Power-Bus (comprising power/ground planes) impedance and fields are evaluated by an efficient series expansion method that is suggested in this paper. It is used to investigate the structure's radiated emission(RE) levels and find acceptable ways of loading the power/ground planes such as decoupling capcitor(DeCap)s, balanced feeding and slits, in order to reduce the interferences. Also, the calculations and measurements of a proposed geometry are verified by vector fitting as a analysis model to check the behavior of the slit.

• 한국정보통신설비학회:학술대회논문집
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• 2007.08a
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• pp.31-33
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• 2007

This work presents the simplified mechanism that the microstrip line generates the radiated emission which is one of the measures on the EMI levels. The electric currents on the metallization of the structure are input to the radiation integrals with the Green's functions being derived to consider the stratification of the microstrip. The simulated results suggest the method of the conceptualization on the RE characteristics of the signal trace in the PCB structure.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.1
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• pp.63-72
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• 2020

As the design complexity and performances are increased in satellite electronic board, noise related problems are also increased. To minimize the noise issues, various design improvements are performed by power integrity and signal integrity analysis in this research. Static power and dynamic power design are reviewed and improved by DC IR drop and power impedance analysis. Signal integrity design is reviewed and improved by time domain signal wave analysis and PCB(Printed Circuit Board) design modifications. And also power planes resonance modes are checked and mitigation measures are verified by simulation. Finally, it is checked that radiated noise is reduced after design improvements by EMC(Electro Magnetic Compatibility) RE(Radiated Emission) measurement results.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1403-1405
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• 2008

In this paper, the preliminary EMC analysis process between the Communication, Ocean and Meteorological Satellite (COMS) and Geostationary Earth Orbit (GEO) launch vehicles in the frequency range [1MHz-47MHz] is described. The considered launch vehicle is the Arian V. The launch vehicle Radiated Emission (RE) specifications have been compared to COMS satellite Radiated Susceptibility (RS) limits. The COMS RS limits are the RS qualification levels of COMS units during launch. As a result, The radiated emission levels of the Arian V is compliant with COMS RS limits.

• Journal of electromagnetic engineering and science
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• v.1 no.2
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• pp.126-130
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• 2001

The performance of a fully anechoic chamber (FAC) for radiated emission (RE) measurements has been evaluated using the normalized site attenuation (NSA). To do this, the antenna factor (AF) of a set consisting of nearly identical antennas has been calibrated at an open area test site (OATS). Appropriate correlation factor (CF) between the chamber and the OATS has been calculated. Results show that the performance of the chamber is fairly good with respect to the ANSI-limit except 41~66 MHz far vertical polarization and near 900 MHz for horizontal polarization.