• 한국위성정보통신학회논문지
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• 제6권1호
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• pp.109-114
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• 2011

2010년 6월에 발사된 천리안통신위성은 한국전자통신연구원이 주도하여 개발된 국내기술개발 시스템으로, 위성발사후 궤도내시험(IOT) 또한 완전히 국내 기술로 수행되었다. 천리안통신위성에 대한 IOT는 크게 안테나패턴 측정과 탑재체의 RF성능시험으로 이루어져, 발사 10일후부터 약 40여일동안 진행되었다. 본 논문에서는 천리안통신위성에 대한 IOT 수행 내용 및 결과에 대해 상세하게 기술하였다. 각 IOT 시험 결과를 지상시험결과와 비교하여 검증하였을 때, Ka대역 탑재체의 IOT 측정은 성공적으로 이루어졌고, 발사후 궤도상에 안착된 천리안통신위성의 모든 채널 상태는 정상임을 알 수 있다.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2002년도 하계종합학술대회 논문집(1)
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• pp.291-294
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• 2002

This paper proposed interface test method for performance verification of communication and broadcasting satellite between communication and broadcasting satellite payload and EGSE(Electrical Ground Support Equipment). We need ground support equipment for test them to performance verification and conform interface function of payload. This paper define tile telemetry transfer method for control payload using GSE(Ground Support Equipment) and receive telemetry data collected from GSE through bus simulator

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2007년도 춘계학술대회논문집
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• pp.220-223
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• 2007

Acoustic test of the payload fairing of Korea satellite launch vehicle was conducted to verify the performance of acoustic protection system installed inside the payload fairing. This paper briefly introduces the acoustic test procedures and its results. Overall 148 dB acoustic loads were exerted on the payload fairing structures which mated with the upper stage structure of the launch vehicle. In order to verify the increase of insertion loss by the acoustic protection system, two kinds of test were performed. One is conducted with acoustic protection system and the other without acoustic protection system. Internal acoustic loads as well as external ones were measured and the measured insertion losses were compared with the requirement. The results showed that the acoustic protection system increases the insertion loss by more than 6 dB above 125 Hz. They also indicated that some design modification of Helmholtz resonator array is required to increase the insertion loss at a cavity resonant frequency.

• 한국항공우주학회지
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• 제31권10호
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• pp.97-104
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• 2003

위성 탑재체의 자체개발 능력을 확보하기 위한 노력의 일환으로 탑재체의 전자파특성이 다른 시스템의 성능에 영향을 주는지와 다른 시스템에 의해 탑재체의 성능이 영향을 받는지를 확인하는 전자파환경시험을 통한 탑재체 시스템의 설계검증을 수행하였다. 기술인증모델(EQM) 통신방송위성(CBS) 탑재체를 대상으로 복사 및 전도 잡음의 분석과 측정을 통하여 시스템 규격의 만족 여부를 확인하였고, 외부 잡음성분에 의한 성능변화를 이론적인 방법과 측정을 통해 검증하여 탑재체의 감응도가 전체 성능에 미치는 영향을 확인하였다. 이러한 분석과 시험을 통해 우주환경에서 운용가능한 수준의 EMC 성능을 확인하고 도파관설계 및 조립방법의 개선을 통해 위성 탑재체의 신뢰성과 안전성을 극대화시킬 수 있다.

• 한국소음진동공학회논문집
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• 제21권12호
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• pp.1146-1151
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• 2011

Acoustic load from rocket propulsion system is main source of random vibration working on the payload. To protect payload from this acoustic load, additional APS(acoustic protection system) is generally applied. Noise reduction capacity of APS can be verified through acoustic test and vibro-acoustic coupled analysis. This paper compared the results of acoustic test and vibro-acoustic coupled analysis about KSLV-I payload fairing with APS.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2011년도 추계학술대회 논문집
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• pp.196-201
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• 2011

Acoustic load from rocket propulsion system is main source of random vibration working on the payload. To protect payload from this acoustic load, additional APS(acoustic protection system) is generally applied. Noise reduction capacity of APS can be verified through acoustic test and vibro-acoustic coupled analysis. This paper compared the results of acoustic test and vibro-acoustic coupled analysis about KSLV-I payload fairing with APS.

• 대한전자공학회:학술대회논문집
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• 대한전자공학회 2000년도 추계종합학술대회 논문집(1)
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• pp.389-392
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• 2000

Electronics and Telecommunications Research Institute (ETRI) developed the Ka-band satellite communications payload. This system is able to provide a high data rate communication service with a bandwidth of 200 MHz, a wideband digital flunking services up to 155 Mbps and asymmetrical internet multimedia service. The system employs the common receive/transmit antenna and the 2-for-1 redundant scheme for the LNA-Downconverters. The different types of high power amplification, TWTA for one chain and SSPA for the other chain, are used lot the variety of experimental options. For the reliable test of the payload, EGSE was also developed. The parametric RF tests were carried out in order to measure the performance of Ka-band communication subsystem, in most case the results of RF performance test complied the payload requirement.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.258-261
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• 2006

The structure of small launch vehicle can be divided into engine section and payload section. This paper introduces modal test of the payload section of small launch vehicle which is composed to satellite, PLA (Payload Adapter), VEB (Vehicle Equipment Bay), KMS (Kick Motor Support) and KM (Kick Motor). From this test, dynamic properties of the 2nd stage structure of small launch vehicle can be obtained. In this test, to simulate free-free boundary condition, test object was hung by 4 bungee cords and excited by using impact hammer Modal test data are analyzed by using TDAS(Test Data Analysis Software). As the result, modal parameters and mode shapes below 100Hz of the 2nd stage of small launch vehicle were identified.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 춘계학술대회논문집
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• pp.717-720
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• 2005

Acoustic loads generated by a rocket propulsion system cause severe random vibrations on payloads. In developing a new launch vehicle, a random vibration level must be specified before the detailed design of payloads or electronic equipments. This paper deals with prediction procedures of a random vibration level on payload section of KSLV-I. The prediction is based on statistical energy analysis. In order to verify the prediction methodology, test and analysis on a sub-scale payload section are performed. The predicted results subject to very high level of acoustic loads show a good agreement with the test results performed in the high intensity acoustic chamber. The predicted random vibration level on payload section of KSLV-I is also presented in this paper.

• 한국항공우주학회지
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• 제39권5호
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• pp.466-473
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• 2011

인공위성의 열제어는 인공위성이 운용궤도상에서 겪는 고진공, 극한의 온도변화 환경에서 위성 구성품의 온도변화를 허용한계 온도 범위 내에서 유지하는데 목적이 있다. 본 연구에서는 저궤도 관측위성(LEO)의 광학탑재체에 대한 열해석 과정으로 열진공 시험 조건, 열진공 챔버의 형상, 위성 탑재체 내부의 열적 환경을 고려하여 열해석 모델을 구성하고 궤도 조건에 따른 열해석을 수행하였다. 또한 광학탑재체의 지상 열진공 시험 조건에 따른 열해석 수행하여 열진공 시험을 위한 시험조건을 정립하였다.