• 한국전자파학회논문지
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• 제23권4호
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• pp.449-456
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• 2012

본 논문에서는 Ka 대역의 다중 단자 증폭기(Multi-port Amplifier: MPA)를 위한 도파관 $8{\times}8$ 버틀러 매트릭스(Butler Matrix: BM)를 설계하였다. 광대역 특성을 구현하기 위해서 버틀러 매트릭스를 구성하는 3 dB 결합기는 6개의 이항식 슬롯을 갖도록 설계하였다. 설계된$8{\times}8$ 버틀러 매트릭스를 제작하여 측정한 결과, 3 GHz의 설계 대역폭 안에서 0.3 dB 이하의 전송 손실과 26 dB 이상의 입력 반사 손실 그리고 35 dB 이상의 격리도 특성을 얻을 수 있었다.

• 한국소음진동공학회논문집
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• 제24권1호
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• pp.5-13
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• 2014

Number of components and payload systems installed in satellites were found to be exposed to various disturbance sources such as the reaction wheel assembly, the control moment gyro, coolers, and others. A micro-level of vibration can introduce jitter problems into an optical payload system and cause significant degradation of the image quality. Moreover, the prediction of on-orbit vibration effects on the performance of optical payloads during the development process is always important. However, analyzing interactions between subsystems and predicting the vibration level of the payloads is extremely difficult. Therefore, this paper describes the analytical and experimental approach to microvibration effects on satellite optical payload performance with integrated jitter analysis frame-work, microvibration emulator and satellite structure testbed.

• ETRI Journal
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• 제46권2호
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• pp.323-332
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• 2024

Receiver and transmitter monolithic microwave integrated circuit (MMIC) multifunction chips (MFCs) for active phased-array antennas for Ka-band satellite communication (SATCOM) terminals have been designed and fabricated using a 0.15-㎛ GaAs pseudomorphic high-electron mobility transistor (pHEMT) process. The MFCs consist of four-channel radio frequency (RF) paths and a 4:1 combiner. Each channel provides several functions such as signal amplification, 6-bit phase shifting, and 5-bit attenuation with a 44-bit serial-to-parallel converter (SPC). RF pads are implemented on the bottom side of the chip to remove the parasitic inductance induced by wire bonding. The area of the fabricated chips is 5.2 mm × 4.2 mm. The receiver chip exhibits a gain of 18 dB and a noise figure of 2.0 dB over a frequency range from 17 GHz to 21 GHz with a low direct current (DC) power of 0.36 W. The transmitter chip provides a gain of 20 dB and a 1-dB gain compression point (P1dB) of 18.4 dBm over a frequency range from 28 GHz to 31 GHz with a low DC power of 0.85 W. The P1dB can be increased to 20.6 dBm at a higher bias of +4.5 V.

• 한국위성정보통신학회논문지
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• 제7권1호
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• pp.116-121
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• 2012

저궤도 기상위성 개발을 위한 기술기준을 도출하기 위하여 이론적으로 접근, 적외선 및 마이크로파 탑재체 센서의 특성 분석하였다. 또한, 저궤도 기상위성 탑재체 개발과 관련하여 현존하는 국외 저궤도 기상위성에 탑재된 마이크로파센서들의 채널요구사항 및 위성체 접속 요구사항을 분석하였다. 본 논문에서는 저궤도 기상위성시스템의 접속 요구사항으로 다목적위성 버스와 소형위성 플렛폼인 CAS 500, 그리고 위성관제시스템의 핵심 서브시스템 및 주요 기능 요구사항을 제시 하였다.

• 한국진공학회:학술대회논문집
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• 한국진공학회 2009년도 제36회 동계학술대회 초록집
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• pp.132.2-132.2
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• 2009

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2002년도 하계종합학술대회 논문집(1)
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• pp.355-358
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• 2002

This paper describe the passive intermodulation products(PIMs) which are formed in high power Ku-band transponder and antenna subsystem on the Communication St Broadcasting Satellite(CBS)program when two transmit carriers beat together to generate harmonics that fall into the receive band. How the PIMs are initially generated and the effect of PIMs for Ku-Band payload system are analyzed by calculating the PIMs frequencies and the power level of PIMs.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.667-676
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• 2009

탑재체 (Payload)는 수동형과 능동형으로 분류되며 , 다양한 형태의 레이더 영상(Radar Image)을 획득하기 위한 위성은 일반적으로 능동형 탑재체인 SAR(Synthetic Aperture Radar)를 이용한다. SAR 위성은 탑재체에서 송신한 전파가 반사되는 것을 획득하여 영상을 형성한다. 때문에 위성이 반사신호를 설계한대로 획득하여 영상을 구성하기 위해서는 궤도에서 실제로 획득한 지상 영상을 기반으로 검보정을 수행하여야 한다. 이에 필요한 것이 지상 목표물인 각면판 반사기(CR; Corner Reflector)이다. 반사기(Reflector)는 다양한 형태가 있으며, SAR를 탑재한 위성의 특성 및 운영목적에 적절하게 설계되어 활용된다. 여기서는 최적의 반사기와 효율적인 반사기들의 특성을 확인하고 그에 대한 고찰을 수행하였다. 또한 그 결과를 바탕으로 삼면판 반사기(Trihedral Corner Reflector)를 설계하고 관련 성능을 확인하였다.

• 대한원격탐사학회지
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• 제18권1호
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• pp.53-59
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• 2002

The MSC is a payload on the KOMPSAT-2 satellite to perform the earth remote sensing. The instrument images the earth using a push-broom motion with a swath width of 15 km and a GSD(Ground Sample Distance) of 1 m over the entire FOV(Field Of View) at altitude 685 km. The instrument is designed to haute an on-orbit operation duty cycle of 20% over the mission lifetime of 3 years with the functions of programmable gain/offset and on-board image data compression/storage. The MSC instrument has one channel for panchromatic imaging and four channel for multi-spectral imaging covering the spectral range from 450nm to 900nm using TDI(Time Belayed Integration) CCD(Charge Coupled Device) FPA(Focal Plane Assembly). The MSC hardware consists of three subsystem, EOS(Electro Optic camera Subsystem), PMU(Payload Management Unit) and PDTS(Payload Data Transmission Subsystem) and each subsystems are currently under development and will be integrated and verified through functional and space environment tests. Final verified MSC will be delivered to spacecraft bus for AIT(Assembly, Integration and Test) and then COMSAT-2 satellite will be launched after verification process through IST(Integrated Satellite Test). In this paper, the introduction of MSC, the configuration of MSC electronics including electrical interlace and design of CEU(Camera Electronic Unit) in EOS are described. MSC Operation parameters induced from the operation concept are discussed and analyzed to find the influence of system for on-orbit operation in future.

• 한국전산유체공학회지
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• 제12권3호
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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.

• Journal of Astronomy and Space Sciences
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• 제16권2호
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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.