• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.10 no.4
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• pp.582-593
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• 1999

This paper presents the design and fabrication of the diplexer for a KOREASAT-III Ka-band satellite transponder. The transmission characteristics of the diplexer is analyzed by calculating the generalized scattering matrix using mode matching method. It is composed of 2 bandpass filters, coupled with H-plane T-junction having symmetrical inductive iris and E-plane metal insert structures. Compared with the size and weight of the Rx and Tx filter loaded with a transponders respectively, those of the diplexer can be effectively reduced. In a high power transmission, the variation of the filter characteristics is minimized by the scheme that irises are extended to the exterior of H-plane of the waveguide. This scheme needs no extra heat sinks for dissipating high power. The diplexer is designed to improve the simplification, durability and reliability by eliminating tuning screws, which have been used to compensate for the characteristics of fabricated filters. The bandpass filters of the diplexer show the insertion loss of less than 1.2 dB and the return loss in excess of 15 dB. The isolations of more than 65 dB have been achieved between Rx and Tx filter.

• Journal of the Korean Institute of Telematics and Electronics D
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• v.36D no.9
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• pp.13-20
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• 1999

A 2-stage MMIC(monolithic Microwave Integrated Circuits) LNA(Low Noise Amplifiers) at 30GHz hand has been designed and fabricated for the Ka-band Satellite Communications. The $0.15 {\mu}m$ with the width of $80 {\mu}m$ pHEMT technology was used for the fabrication of this MMIC LNA. Using the series feedback technique, ultra low noise and excellent S11 could be obtained at the same time without the cost of gain at 30GHz-band. The stability factors(Ks) for each stage and overall stage are greater than 1 at full frequency bands by the bias circuits and stabilization circuit. The measured performances, which agree well with the predicted performances, show this 2-stage MMIC LNA has the gain of more than 15.7dB and noise figure of less than 2.09dB over 29GHz to 33GHz.

• Journal of Aerospace System Engineering
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• v.1 no.3
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• pp.1-6
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• 2007

The COMS(Communication, Ocean & Meteorological Satellite)is the geostationary satellite which will be performing three main objectives such as meteorological service, ocean monitoring and Ka-band satellite communications. This paper presents the analysis of the electromagnetic radiated compatibility between COMS satellite and the ARIANE 5 launch vehicle. As a conclusion, a good level of confidence can be given at present time to demonstrate the compatibility between the spacecraft and the launcher, and vice versa. No threat has been identified regarding the other units powered during launch mode.

• ETRI Journal
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• v.27 no.1
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• pp.43-52
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• 2005

In this paper, we introduce an adaptive radio resource allocation for IP-based mobile satellite services. We also present a synchronous multibeam CDMA satellite system using an orthogonal resource sharing mechanism among downlink beams for the adaptive packet transmission. The simulation results, using a Ka-band mobile satellite channel and various packet scheduling schemes, show that the proposed system and resource allocation scheme improves the beam throughput by more than two times over conventional systems. The simulation results also show that, in multibeam satellite systems, a system-level adaptation to a user's channel and interference conditions according to user locations and current packet traffic is more efficient in terms of throughput improvement than a user-level adaptation.

• Journal of IKEEE
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• v.3 no.1 s.4
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• pp.1-10
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• 1999

In this paper, the design for the shaped offset cassegrain antenna system combined with corrugated feed horn is presented. First, spherical-mode wave theory is applied to the corrugated conical horn and its radiation patterns are investigated. Using the radiation patterns, design data of the corrugated conical horn are obtained by efficiency investigation of horn antenna. When the investigation is completed, the flare angle and length of the corrugated conical horn is determined. Next, the main and sub-reflector is designed using Snellis law and the conservation principle of energy. Then the uniform direction and energy density of the traveling wave at the aperture of the main-reflector is obtained. The maximum size of the main-reflector is determined by investigation of the illumination and spillover efficiency. Finally, the curvature of the main-reflector is modified to satisfy the condition of the uniform phase. From the calculated efficiencies, the designed site of the main-reflector and sub-reflector, system gain of the shaped offset cassegrain antenna has been obtained 40.5dB in Ka-band frequency. It has better characteristics than the result of SABOR with 39dB gain.

• Journal of electromagnetic engineering and science
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• v.10 no.3
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• pp.175-178
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• 2010

In this paper, a millimeter-wave multi-beam antenna is studied by rotating the antipodal linear tapered slot antenna(ALTSA) with respect to a center is successfully designed. In order to lowering the SLL and enhancing the isolation between the ALTSA elements, a row of metallic via is inserted between the ALTSAs. A 9 beams antenna is designed and experimented at Ka band. The measured and simulated results agree well with each other. The antenna can provide horizontal wide angle coverage up to ${\pm}62^{\circ}$. The gain of each beam can achieve about 12.5 dB. The mutual coupling between ports is all below 20 dB.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.25.3-25.3
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• 2011

지구 또는 우주 원격탐사 및 관측에서 진일보한 임무 수행을 위해 위성 편대 비행의 필요성이 점차 부상하고 있다. 편대 비행은 단일 위성으로는 실현하기가 어렵거나 불가능한 과학적인 임무를 수행할 수 있다. 다양한 위성 편대 비행 기술에서 중요한 기술 중에 하나는 편대 위성간의 정밀기선결정 기술이며, 정밀도 검증 기술도 함께 동반되어야 한다. 이 논문에서는 Gravity Recovery and Climate Experiment(GRACE) 위성의 실제 Global Positioning System(GPS) 데이터를 사용하여 GRACE A와 B 두 위성의정밀기선결정을 수행하였다. 그리고 K/Ka-Band Ranging system(KBR) 바이어스 거리측정값으로 일괄처리 및 순차처리 방법을 통해 정밀도를 검증하였다. 제안된 순차처리 방법은 KBR 바이어스를 추정하는 대신에 기산점 차분으로 이를 제거하여 정밀도를 검증하기 때문에 검증자(KBR baised range)가 피검증자(GPS-baseline)와 독립적이고 실시간 정밀도 검증에 적용이 가능하다. 그 결과 일괄처리 검증방법과 유사한 1.5 ~ 3.0 mm의 순차처리 정밀도 검증 결과를 얻었다.

• Journal of electromagnetic engineering and science
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• v.5 no.4
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• pp.176-182
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• 2005

In this paper, an efficient multipaction analysis method of a manifold multiplexer for satellite applications is presented. While FEM(Finite Element Method) is used for the multipaction analysis of the lowpass filter, the equivalent circuit model is used for the analysis of the channel filters and the manifold. Employing equivalent circuit model for multipaction analysis takes less time than using EM(Electromagnetic) field analysis method while keeping the accuracy of the multipaction analysis. This present analysis method is applied to the manifold multiplexer for Ka-band satellite transponders and the results show that the present method is as accurate as the conventional EM field analysis method.

• Proceedings of the KIEE Conference
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• 2008.10b
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• pp.369-370
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• 2008

The Payload Interface Unit (PIU) provides the interface between payload equipment (GOCI, MODCS and Ka Band P/L) and the SCU. The PIU is a MIL-STD-1553-Bus Remote Terminal (RT). The MPIU distributes commands to, acquires telemetry from and takes part in the thermal control of the payload equipment. When in ON mode, the PIU is completely observable and can be used for payload control. When in OFF mode, the PIU is non active except the thermal control electronics.

• International Journal of Aeronautical and Space Sciences
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• v.3 no.2
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• pp.40-45
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• 2002

A radiation analysis is performed for the Ka and Ku-band transponder of the Communications and Broadcasting Satellite (CBS) that is planned for launch into the geo-synchronous orbit. A particular attention is given to calculation of Total Ionizing Dose (TID) for the mission life time of 15 + 3 years. A numerical modeling of the charged particles at the geo-synchronous orbit is undertaken. The charged particles from the modeling are then transported through the mechanical structure and component housings of the transponder. A set of locations are selected for the detailed calculation of TID. The results from the present calculation show that three-dimensional modeling of the component housings as well as the mechanical structure of the spacecraft is requisite in order to acquire a reliable calculation of TID.