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A BUS System Conceptual Design of Experimental Communication Satellite
Kim, Zeen-Chul,Choi, Seong-Bong,Nam, Mun-Kyung,Yang, Koon-Ho,Choi, Jae-Dong 통신위성우주산업연구회 2000 Joint Conference on Satellite Communications Vol.2000 No.-
The 2005SAT is designed to fit within the standard fairings for all compatible launch vehicles including Ariane IV, V and Atlas II/III. The 2005SAT configuration is compatible with single launch, upper or lower position of dual launch. Two offset-fed Gregorian antennae are located on the earth panel of the 2005SAT for Ku-band and Ka-band communication services. The 2005SAT bus is 3-axis stabilized platform both for transfer orbit and on-orbit operations. The attitude control logic is used quaternion using gyro data and have the compensation logic for gyro bias update by the ESA and the SSA data. The 200SSAT Electrical Power Subsystem (EPS) is designed a regulated directed-energy transfer configuration that minimize the losses between the solar array and loads while minimizing the complexity and mass of load power converters. The duel-mode propulsion scheme is selected for 2005SAT. TC&R subsystem is conceptually designed to determine specifications of processor speed, RAM and ROM size, command-telemetry format and data bus type
김진철(Kim Zeen-Chul),김한돌(Kim Han-Dol),용상순(Yong Sang-Sun) 대한전자공학회 1992 대한전자공학회 학술대회 Vol.1992 No.10
This paper describes satellites' three main stabilization techniques namely gravity gradient method, spin stabilization method and three-axis stabilization method. In conjunction with the methods, dynamic modelling and simulation was performed to characterize the pointing performance of each method. The trade-off between the methods was also compared in the sense of accuracy and complexity.
효율적인 다물체 동역학 해법 및 인공위성 전개장치에의 응용
이기수(Kisu Lee),김진철(Zeen Chul Kim) 대한전자공학회 1992 대한전자공학회 학술대회 Vol.1992 No.10
Solar arrays and antennas of the satellite are usually stowed within the dimensions of the launch-vehicle fairing and deployed in the orbit. To solve such multibody dynamic problems, differential equations and algebraic equations are simultaneously solved, and special solution techniques are required. In this paper, Lagrange multipliers associated with the constraints are iteratively computed by monotonically reducing an appropriately defined constraint error vector, and the resulting equation of motion is solved by a well-established ODE technique. Deformable bodies as well as rigid bodies are treated, and applications to satellite solar arrays are explained.
심우주 지구 반사율 측정용 아몬라 가시광 채널의 광학 시스템 제조 및 성능 평가
Park, Won-Hyun,Kim, Seong-Hui,Lee, Han-Shin,Yi, Hyun-Su,Lee, Jae-Min,Ham, Sun-Jung,Yoon, Jee-Yeon,Kim, Sug-Whan,Yang, Ho-Soon,Choi, Ki-Hyuk,Kim, Zeen-Chul,Lockwood, Mike,Morris, Nigel 한국우주과학회 2007 Journal of Astronomy and Space Sciences Vol.24 No.1
지구와 태양 사이의 중력 평형점에서 혜일로 궤도로 운용되며, 심우주 반사율(albedo)을 측정코자 하는 EARTHSHINE 미션의 과학적 목적에 최적화된 아몬라 가시광 채널의 성능 인증 모델용 광학 시스템 개발을 완료하였다. 아몬라 광학계 설계 요구사항에 부합하는 설계안과 공차분석 결과를 바탕으로 광학 시스템의 설계, 부품 제작, 결합, 정렬, 성능 검증까지의 전 공정을 순수 국내 개발하였으며 특히 측정된 부품들의 광파면 오차를 결합 및 성능 평가 공정에 역투입하는 신 공법에 의하여 성능 검증을 실시하였다. 최종 결합 및 정렬이 완료되어 측정한 아몬라 광학계의 광파면 오차는 중심 시야에서 RMS 0.091 wave(기준 파장: 632.8nin)이며, Ensquared Energy(EE) 성능은 61.7%($14{\mu}m$ 이내), 변조전달함수(MTF) 성능은 35.3%(기준 주파수: $35.7mm^{-1}$)이다. 위 결과들은 아몬라 가시광 채널의 요구사항을 모두 만족시킴으로써 개발된 아몬라 가시광 채널 광학계가 EARTHSHINE 미션의 과학목적을 완수할 수 있음을 증명하였다. The AmonRa instrument, the primary payload of the international EARTHSHINE mission, is designed for measurement of deep space albedo from L1 halo orbit. We report the optical design, tolerance analysis and the optical performance of the breadborad AmonRa imaging channel instrument optimized for the mission science requirements. In particular, an advanced wavefront feedback process control technique was used for the instrumentation process including part fabrication, system alignment and integration. The measured performances for the complete breadboard system are the RMS 0.091 wave(test wavelength: 632.8 nm) in wavefront error, the ensquared energy of 61.7%($in\;14\;{\mu}m$) and the MTF of 35.3%(Nyquist frequency: $35.7\;mm^{-1}$) at the center field. These resulting optical system performances prove that the breadboard AmonRa instrument, as built, satisfies the science requirements of the EARTHSHINE mission.