• 한국철도학회:학술대회논문집
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• 한국철도학회 2007년도 춘계학술대회 논문집
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• pp.1239-1243
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• 2007

Autonomous Station Control System is automatic route control system of large-scale station. The system has flexibility of system step-by-step construction and expandability. A method of step-by-step construction for Autonomous Station Control System has system expansion and subsystem software expansion. The system has autonomous controllability and autonomous coordinability for system step by step construction. With property for a basis, each of subsystem communicates data field. Also, Each subsystem has its own management system, Autonomous Data Manager to manage itself and coordinate with the others. This paper make clear test method for Autonomous Station Control System expansion and software expansion. The first test method of system increasing construction is single station construction test. The second of method is connecting test the neighbor's Autonomous Station Control System. The third of method is connecting test the Autonomous Line Management System. Also, the test method of software expansion take the case of route control subsystem.

• 한국위성정보통신학회논문지
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• 제2권2호
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• pp.36-40
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• 2007

EGSE is used to check out satellite payload during the development prior to launch. The EGSE represented in this paper is a test system for Ka band communication transponder of COMS. The EGSE consist of two subsystems as CTS subsystem and PCTS subsystem. Communication Test subsystem (CTS) performs satellite transponder RF performance testing, data analysis and trending. Most of transponder RF performances are automatically tested by the CTS subsystem. Power, Command & Telemetry subsystem (PCTS) monitor telemetry messages from the transponder and send tele-commands to satellite transponder for the configuration change. PCTS also provide simulated S/C power to the transponder during the ground validation testing. The EGSE test functions are verified by the transponder simulator testing and will be used for the flight model transponders testing.

• ETRI Journal
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• 제27권2호
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• pp.140-152
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• 2005

In this paper, we present design features, implementation, and validation of a satellite simulator subsystem for the Korea Multi-Purpose Satellite-2 (KOMPSAT-2). The satellite simulator subsystem is implemented on a personal computer to minimize costs and trouble on embedding onboard flight software into the simulator. An object-oriented design methodology is employed to maximize software reusability. Also, instead of a high-cost commercial database, XML is used for the manipulation of spacecraft characteristics data, telecommand, telemetry, and simulation data. The KOMPSAT-2 satellite simulator subsystem is validated by various simulations for autonomous onboard launch and early orbit phase operations, anomaly operation, and science fine mode operation. It is also officially verified by successfully passing various tests such as the satellite simulator subsystem test, mission control element system integration test, interface test, site installation test, and acceptance test.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.489-492
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• 2005

As a former level of MSC(Multi Spectral Camera) telescope of the KOMPSA T2satellite, the several performance tests of EOS(Electro Optical Subsystem) were performed in the EOS level. By these tests, not only the design requirement of payload can be verified but also the test result can be the important criterion to estimate the performance of payload in the launch and space orbit environment. The EOS Geometric Mapping test is to verify the accuracy of the alignment & assembly on the Subsystem of the MSC by measurement like these; LOS(Line of Sight), LOD(Line of Detector), Band to Band Registration, Optical Distortion and Reference Cube. This paper describes the test results and the analysis for the EOS Geometric Mapping.

• 항공우주기술
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• 제12권2호
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• pp.14-23
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• 2013

위성 운용 중 발생할 수 있는 오류에 대한 대비를 고장 관리 설계라고 한다. 고장 관리 설계는 위성에 이상 현상이 나타나는 경우 감지하고 고립시키며, 지상에서 위성과 접속한 이후 오류 사항을 파악하고 대응책을 마련할 때까지 위성을 안전한 상태로 유지하는 기능을 포함한다. 안전 모드 운용은 정상 운용과는 다르게 비행 소프트웨어를 탑재한 탑재 컴퓨터와 전력 제어 및 분배 장치 주관 하에 지상국의 접속 없이 이루어진다. 오류 발생 시 고장 관리 설계에 따라 자동화된 동작이 이루어지는 만큼 지상 시험 단계에서 고장 관리 로직 및 관련 하드웨어가 설계된 대로 동작하는지를 철저하게 검증해야 한다. 또한 실제와 유사한 오류를 위성에 손상 없이 인가해야 한다. 고장 관리 설계 검증시험은 위성을 구성하는 다양한 부분체에 대해서 수행되나 본 논문에서는 저궤도 위성의 비행 모델을 대상으로 수행된 자세제어계와 전력계 시험의 설계에 대해 서술하고 결과에 대해 정리하였다.

• 한국산업융합학회 논문집
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• 제3권3호
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• pp.251-256
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• 2000

This report analyzes the Source Qualification Test which is composed of main functional and environmental tests for the localizing avionics(electronic subsystem for aircrafts and spacecraft) and high performance mechanical subsystem. Especially the detail test approaches of integrated servo actuators which is the main part to supply the power to the main and other flying control panel. Nowadays this subsystem works with mechanical and electrical engineering technique. In detail, electrical signal is used as input and transferring tool and mechanical part is the output as a power and manufacture the physical dimensions and functions. Finally in this review, the new test procedure to prove the function by the new manufacturer is established.

• 한국군사과학기술학회지
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• 제10권2호
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• pp.84-89
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• 2007

MIL-STD-461E, EMI military standard for the equipment and subsystems, requires reception characteristic tests to verify the susceptibility of a receiver against the jntermodulation and spurious signals. Because the CS103 and CS104 of MIL-STD-461E show the test configuration of the equipment unit like a traditional receiver, it is possible to verify the susceptibility only for the reception signal through analog filters. However, at present when software programming techniques make a progress, the CS103 and CS104 tests need to evaluate the reception signal of the subsystem which includes both the digital filtering effects and analog filter characteristics. These test and evaluation techniques applied to a surveillance radar subsystem. This paper researched the EMI test methods in order to confirm feasibility of these test and evaluation techniques. Also the test results are compared and analyzed.

• International Journal of Aeronautical and Space Sciences
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• 제5권1호
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• pp.6-18
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• 2004

This paper addresses the development and design of the HAUSAT-l (Hankuk Aviation University SA'Tellite-D communication subsystem, which is a next generation picosatellite, developed by SSRL (Space System Research Lab.) of Hankuk Aviation University. The communication subsystem generally consumes the majority of power and volume for picosatellites, and thus its design is critical to the overall satellite and mission plans. The HAUSAT-l designs are implemented by using the 145.84 MHz for uplink and 435.84 MHz for downlink frequency bands. The simulation and test results of the homemade radio and the TNC (Terminal Node Controller) integrated on the HAUSAT - I , a picosatellite scheduled to launch on September 2004 by Russian launch vehicle "Dnepr", are presented for EM, QM and FM, respectively.

• 한국산업정보학회논문지
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• 제19권1호
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• pp.31-41
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• 2014

정지궤도위성은 다수의 탑재체를 하나의 위성체 플랫폼에 탑재하고 2010년 6월 26일에 발사되었다. 전력계는 태양 및 식 기간 상태에서 완전 조절 $50V_{DC}$ 전력 버스를 제공한다. 위성에서 요구되는 전력은 태양전지 배열기 윙에서 생성되며, 에너지는 192.5Ah 용량의 리튬-이온 배터리에 저장된다. 본 논문은 전력계의 성능 평가를 향후 정지궤도위성 설계에 활용하기 위해 전력계의 중요 설계 변수들을 선정하고, 지상에서 시험 결과와 궤도상에서 운영 결과를 비교 분석하였다. 설계로부터 궤도상에서 운영 결과까지의 성능 평가를 통해 전력계는 중요한 성능감소 없이 정상적으로 동작되고 있음을 입증하였다.

• Journal of Astronomy and Space Sciences
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• 제15권2호
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• pp.499-508
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• 1998

다목적 실용위성 관계시스템의 SOS(Satelite Operations Subsystem) 서브시스템은 위성에서 보내온 원격측정 데이터를 처리하여 위성의 상태를 감시하고 위성으로 원격명령을 전송하는 업무를 수행한다. 본 논문에서는 SOS 서브시스템의 신뢰성 및 가용성을 향상시키기 위하여 하드웨어와 소프트웨어를 이중화하여 데이터 손실을 최소화하도록 설계한 SOS의 동족 고장관리(dynamic fault management) 기법에 대하여 기술하였다. 또한 구현의 정당성을 확인하기 위한 성능 시험 방법을 제시하였으며 그에 대한 결과를 분석하였다.