• 한국전산유체공학회지
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• 제20권4호
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• pp.63-69
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• 2015

The thermal balance test in vacuum chamber for satellite structures is an essential step in the process of satellite development. However, it is technically and economically difficult to fully replicate the space environment by using the vacuum chamber. To overcome these limitations, the thermal analysis through a computer simulation technique has been conducted. The CFRP composite material has attracted attention as satellite structures since it has advantages of excellent mechanical properties and light weight. However, the nonuniform nature of the thermal conductivity of the CFRP structure should be noted at the step of thermal analysis of the satellite. Two different approaches are studied for the thermal analyses; a detailed numerical modeling and a simplified model expressed by an effective thermal conductivity. In this paper, the effective thermal conductivities of the CFRP composite structures are extracted from the detailed numerical results to provide a practical thermal design data for the satellite fabricated with the CFRP composite structure. Calculation results of the surface temperature and the thermal conductivities along x, y, z directions show fairly good agreements between the detailed modeling and the simplified model for all the cases studied here.

• Journal of Astronomy and Space Sciences
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• 제10권2호
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• pp.103-112
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• 1993

The KITSAT-1 was successfully launched on August 11, 1992, into a near circular, 1300-km-high orbit with an $66^{\circ}$inclination. The satellite carries a solid state detector module to measure the high energy particle flux originating mostly from the inner radiation belt. We describe here the objectives of the experiment, the detector structure, and the preliminary result.

• 한국정보통신학회논문지
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• 제16권8호
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• pp.1631-1641
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• 2012

위성통신에서 이용 효율을 높이기 위해 Time division multiple access (TDMA)를 사용하였으며, 대표적으로 Digital Video Broadcasting- Satellite Second Generation (DVB-S2) 등으로 표준화되어 운용되어 왔다. 본 논문에서는 이미 표준화된 DVB-S2를 직접 사용하기 어려운 특수한 용도의 시스템이 필요하였고, 이를 위하여 다소 주파수 운용효율 저하를 감수하더라도 열악한 전파환경에서도 신뢰성있게 운용이 가능한 TDMA 프레임 구조를 연구하였다. 프레임 주기가 12초로 수~수십 msec인 일반적인 TDMA 시스템 프레임 구조와 차이가 많고, 이에 따른 시간 및 주파수 드리프트 등을 고려하였다. 그리고 주파수 옵셋이 25 kHz이고 낮은 Signal To Noise Ratio(SNR) 에서도 초기 타이밍 동기 및 주파수와 페이저 초기 동기를 확보하는 방식을 제시하였다. 이를 검증하기 위하여 시뮬레이션 및 연동시험을 수행한 결과 SNR -2.5 dB에서도 안정적으로 동기가 확보됨을 알 수 있다.

• 한국통신학회논문지
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• 제39C권4호
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• pp.380-386
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• 2014

본 논문은 Ku대역 모노펄스 위성추적을 위한 동축구조 도파관 고차모드 커플러를 제안하였다. 제안된 고차모드 커플러는 이동체 탑재용 위성추적시스템에 적용 가능하도록 소형/경량화를 위하여 동축구조의 도파관을 이용하였다. 기본모드 신호 추출을 위해 내측 원형도파관을 이용하였고, 고차모드 신호 추출을 위해 외측 원형도파관에 내어진 4개의 슬롯과 스텝 구조의 직사각형 도파관을 이용하였다. 제안된 고차모드 커플러의 모의실험 결과는 반사손실 및 삽입손실이 약 250 MHz의 대역폭(12.75~13.00 GHz)을 만족하며, 모노펄스 추적에 적용 가능한 기본모드 패턴 및 고차모드 패턴이 만족스럽게 생성된 결과를 확인하였다. 제안된 Ku대역 동축구조 도파관 고차모드 커플러는 고속 정밀추적이 요구되는 모노펄스 위성추적시스템에 이용될 것으로 기대된다.

• 항공우주시스템공학회지
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• 제7권2호
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• pp.1-7
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• 2013

Recently, there are a number of studies over dynamic analysis for minimizing vibration of flexible structures such as solar panel for agility of high-agility satellite. The traditional studies perform dynamic analysis of a solar panel assumed as rigid structure since the stiffness of solar panel is higher than the stiffness of solar panel's hinge spring. However, there are vibrations that have modes of bending and torsion when high-agility satellite rotate speedily. This vibrations result in delaying safety time of satellite or degrading image quality. This paper presents dynamic analysis's technique of satellites including the spring hinge of solar panel and flexible structural solar panel's effects described as the linear equation of motion using Lagrange's theorem, and verifies the validity of an established dynamic analysis's technique of satellites by comparing the finite element method. In addition high-agility satellite's dynamic characteristics of a torque profile are analyzed from the established dynamic analysis's technique of satellites.

• 한국위성정보통신학회논문지
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• 제10권4호
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• pp.52-57
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• 2015

국가환경위성센터 지상국 개발을 위한 기술기준을 도출하기 위하여 국가환경위성센터 구축을 위한 입지 조건과 향후 개발될 국가환경위성센터 지상국 특성을 분석하였다. 또한, 국가환경위성센터 지상국 특성 분석을 통하여 지상국 시스템의 구성과 내부인터페이스를 도출하였다. 본 논문에서는 국가환경위성센터 운영에 필요한 환경위성지상국의 상위 요구사항과 환경위성지상국 및 위성관제국 간의 인터페이스 요구사항을 제시하였다.

• 전기학회논문지
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• 제63권2호
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• pp.257-260
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• 2014

In this paper, a high gain waveguide array antenna combining horn antenna on slot radiator was designed. And the fabricated antenna showed enough gain, improved efficiency and broadband characteristics for receiving satellite signals, compare to conventional microstrip antenna which has dielectric loss and radiation loss on transmission line. For easy fabrication, the waveguide structure was composed by 3-stages of radiator, signal coupler and transmission line. By experiment, the array waveguide antenna of 4 by 16 showed 28.3[dBi] gain and 2:1 of VSWR. And by combining horn antenna structure, the gain was increased 1[dB]. The received signal from Koreasat 6 by measurement showed 16[dBc] of C/N on BS(Broadcasting Satellite)-band and 14[dBc] of C/N on CS(Communication Satellite)-band.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2013년도 춘계학술대회 논문집
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• pp.533-539
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• 2013

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 framework, micro vibration emulator and satellite structure testbed.

• Journal of Astronomy and Space Sciences
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• 제40권4호
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• pp.225-235
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• 2023

This paper presents the structural design of a planar synthetic aperture radar (SAR) antenna applied to a microsatellite. For micro-satellite applications, the SAR antenna structure must be lightweight, flat, and designed to withstand the launch environment. To satisfy these conditions, our novel antenna structure was designed using aluminium (AL) alloy. Structural analysis was performed for quasi-static load, random vibration, and shock load to verify its robustness in the launch environment, and the results are presented here.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1995년도 Proceedings of the Korea Automation Control Conference, 10th (KACC); Seoul, Korea; 23-25 Oct. 1995
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• pp.444-447
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• 1995

The satellite in a circular orbit about a planet with disturbances and a three-degree-of-freedom (3DOF) structure under seismic excitations are modeled by the linear stochastic differential equations. Then the risk-sensitive optimal control method is applied to those equations. The mean and the variance of the cost function varies with respect to the risk-sensitivity parameter, .gamma.$_{RS}$ . For a particular risk-sensitivity parameter value, risk-sensitive control reduces to LQG control. Furthermore, the derivation of the mean square value of the state and control action are given for a finite-horizon full-state-feedback risk-sensitive control system. The risk-sensitive controller outperforms a classical LQG controller in the mean square sense of the state and the control action.