• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.155-164
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• 2002

• ICROS
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• v.3 no.5
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• pp.51-57
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• 1997

항공우주분야의 제어는 크게 항공기, 헬리콥터, 발사체, 미사일, 인공위성 등으로 비행체의 특성에 따라 크게 구분된다. 이러한 항공우주 시스템 설계시에는 다른 시스템 설계시와 동일하게 성능 요구조건을 설정한 후에 자동조정 장치를 설계하게 된다. 항공기의 경우에는 비행성과 조종성으롤 크게 구분하여 요구조건이 주어진다. 본 고에서는 항공기 비행제어에 적응제어가 어떻게 사용되었는가에 대하여 소개하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.5
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• pp.432-439
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• 2015

MEMS solid thruster module is composed of solid thruster and its control board. It was developed for the purpose of an academic research. Therefore, thermo-mechanical design and verification for space usage were not considered in the design phase. To mount it on a cube satellite without any design modification, technical efforts at the system level structure design is required. In this study, we proposed a structural design concept to mount the MEMS thruster module by using brackets for guaranteeing structure safety under launch loads and easier mating and de-mating of MEMS thruster module during test phase. The effectiveness of the design has been verified through structural analysis and vibration test. In addition, electrical connection method using spring pins between MEMS thruster and control board is effective for guaranteeing the structural safety under launch vibration loads.

• The Proceeding of the Korean Institute of Electromagnetic Engineering and Science
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• v.14 no.3
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• pp.58-69
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• 2003

위성 통신의 수요가 증가하고 있고, 무궁화 위성 등 우리 위성이 발사되면서 위성 탑재체의 국내 개발이 꾸준히 진행되고 있다. 위성 탑재체의 채널 성능은 채널 필터와 입출력 멀티플렉서의 주파수 특성에 의해 크게 좌우된다. 이 글에서는 채널 필터와 멀티플렉서의 구성과 설계에서의 고려 사항에 대해 검토하겠다. 채널 필터를 포함하는 멀티플렉서는 전기적 설계뿐만 아니라 기계적, 열적 설계에서도 까다로운 사양을 요구하고 있다. 채널필터는 소형 경량화의 요구에 따라 주로 이중 모드(dual mode) 필터로 설계되고 있고, 최근에는 HTS 필터에 의한 설계도 시도되고 있다. 입력 멀티플렉서는 채널 사이의 간섭을 방지하기 위해 써큘레이터를 이용하여 구성하고, 출력 멀티플렉서는 손실을 최소화하기 위하여 매니폴드(manifold)를 이용하여 채널필터를 결합한다. 이 글은 Kunes와 Kudsia의 논문을 주로 참조하였다.

• Journal of Astronomy and Space Sciences
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• v.20 no.4
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• pp.339-350
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• 2003

Engineering qualification model payload for a communications and broadcasting satellite(CBS) was developed by ETRI from May, 2000 to April, 2003. For. the purpose of functional test and verification of the payload, a real-time hardware-in-the-loop(HITL) CBS simulator(CBSSIM) was also developed. We assumed that the spacecraft platform for the CBSSIM is a geostationary communication satellite using momentum bias three-axis stabilization control technique based on Koreasat. The payload hardware is combined with CBSSIM via Power, Command and Telemetry System(PCTS) of Electrical Ground Support Equipment(EGSE). CBSSIM is connected with PCTS by TCP/IP and the payload is combined with PCTS by MIL-STD-1553B protocol and DC harness. This simulator runs under the PC-based simulation environment with Windows 2000 operating system. The satellite commands from the operators are transferred to the payload or bus subsystem models through the real-time process block in the simulator. Design requirements of the CBSSIM are to operate in real-time and generate telemetry. CBSSIM provides various graphic monitoring interfaces and control functions and supports both pre-launch and after-launch of a communication satellite system. In this paper, the HITL simulator system including CBSSIM, communications payload and PCTS as the medium of interface between CBSSIM and communications payload will be described in aspects of the system architecture, spacecraft models, and simulator operation environment.

• Journal of Satellite, Information and Communications
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• v.6 no.2
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• pp.1-9
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• 2011

The Communication Ocean and Meteorological Satellite(COMS), the first geostationary observation satellite, was successfully launched on June 27th in 2010. The raw data of Meteorological Imager(MI) and Geostationary Ocean Color Imager(GOCI), the main payloads of COMS, is delivered to end-users through the on-ground processing. The COMS Image Data Acquisition and Control System(IDACS) developed by Korea Aerospace Research Institute(KARI) in domestic technologies performs radiometric and geometric corrections to raw data and disseminates pre-processed image data and additional data to end-users through the satellite. Currently the IDACS is in the nominal operations phase after successful in-orbit testing and operates in National Meteorological Satellite Center, Korea Ocean Satellite Center, and Satellite Operations Center, During the in-orbit test period, validations on functionalities and performance IDACS were divided into 1) image data acquisition and transmission, 2) preprocessing of MI and GOCI raw data, and 3) end-user dissemination. This paper presents that IDACS' operational validation results performed during the in-orbit test period after COMS' launch.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.5
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• pp.388-396
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• 2019

This paper describes the RF(Radio Frequency) interference on the GNSS receiver due to the S-band signals transmitted from the transmitters in the Test Launch Vehicle, and analyzes the cause of the RF interference. Due to the S-band signals that have relatively high power levels compared with GNSS signals, an LNA(Low Noise Amplifier) in the active GNSS antenna was saturated, and the intermodulation signal within GNSS in-bands was produced in the LNA whenever two S-band signals were received from the GNSS antenna. For these reasons, the C/N0 of the satellite signals in the GNSS receiver was attenuated severely. The design of the LNA was changed in order to protect the RF interference due to the S-band signals and the suppression capability of the RF interference was confirmed in the new LNA through the comparison of the old LNA.

• Journal of Aerospace System Engineering
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• v.17 no.2
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• pp.86-93
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• 2023

Pyrotechnic separation devices have been widely used as holding and release mechanism for deployable appendage. However, pyro-shock can cause temporal or permanent damage on shock sensitive components such as electronics, mechanism, and brittle components. This study proposed a low-stiffness blade based passive shock absorber using a multi-layered stiffener laminated with viscoelastic acrylic tapes for reducing transmitted pyro-shock upon explosion of pyrotechnic separation devices. The multi-layered structure with viscoelastic tape has high-damping characteristics to effectively secure structural integrity of low-stiffness blades under the launch environment. The design effectiveness was verified through a shock test by dropping a pendulum. The structural integrity of the shock absorber under a launch environment was evaluated through structural analysis under load conditions with a deployable payload.

• Proceedings of the KSRS Conference
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• 2008.03a
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• pp.35-38
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• 2008

2010년 발사 예정인 다목적위성 5호의 주 탑재체는 SAR (Synthetic Aperture Radar)이다. 다목적위성 5호의 영상자료 품질을 확보하기 위해 SAR 영상자료에 대한 발사 후 검보정이 현재 한국항공우주연구원에서 준비 작업이 진행 중이다. 본 논문에서는 다목적 위성 5호 검보정 준비 작업 중에서 검보정 site에 대한 시뮬레이션 결과에 대해 설명하고자 한다. SAR 위성 검보정 작업을 위해서는 Corner Reflector가 필수 검보정 장비이고, Corner Reflector(CR)를 다목적위성 5호 beam들의 incidence angle에 따라 적절한 개수를 적절한 위치에 검보정 site 요구조건을 만족하는 위치에 배치해야한다. 한반도내에 15개의 CR들을 가장 요구조건에 만족할 수 있는 적절한 위치에 배치한 후에, 다목적위성 5호의 검보정 site에 대한 시뮬레이션을 수행해 본 결과, 15개의 CR만으로는 다목적위성 5호의 beam들을 모두 검보정할 수 없다는 것을 확인할 수 있었다. 결론적으로 검보정 site 요구조건을 좀 더 만족하고 CR의 개수를 30개 이상 배치할 수 있는 몽고 등의 외국 지역까지 확인해 볼 필요성이 있다.

• Journal of Astronomy and Space Sciences
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• v.16 no.1
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• pp.79-88
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• 1999

The satellite experiences the severe launch environment such as vibration, acceleration, shock, and acoustics induced by rocket. Therefore, the satellite should be designed and manufactured to endure such severe launch environments. In this paper, we describe the structure of the KITSAT-3 FM(Flight Model) and the processes and results of the launch environmental test to ensure the reliability during launch period.