• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.65-65
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• 2003

본 논문에서는 국제우주정거장의 데이터 인터페이스 구현 및 시험을 위하여 1553B와 FDDI 하드웨어를 이용한 시뮬레이터를 제작하였다. 데이터 인터페이스 시뮬레이터는 국제우주정거장과 탑재모듈에 대한 시뮬레이터와 탑재모듈의 제어부분, 상태를 확인하기 위한 모니터링 부분으로 구성되어진다. 국제우주정거장 시뮬레이터는 탑재모듈에 명령을 내리고 상태데이터를 받아 분석하며 탑재모듈에서 수집된 데이터를 수신하여 저장하는 기능을 갖는다. 탑재모듈은 국제우주정거장에서 오는 탑재 수집 데이터를 받아 분석/수행하고 탑재모듈에서 수집된 데이터를 시뮬레이션 하는 기능을 가지며, 모니터링 시스템은 데이터 통신간의 인터페이스 속도나 상태 등을 분석하고 전체적인 그래픽 인터페이스를 제공한다. 본 논문에서는 기존의 PC환경에서 직렬통신과 TCP/IP를 이용하여 시뮬레이션 한 것을, PCI 카드 타입의 1553B와 FDDI 데이터 인터페이스 하드웨어를 이용하여 구현하고 시험하였다. 시뮬레이터 시험 및 검증을 위해서 4가지 타입의 명령을 만들었으며, 국제우주정거장 모듈에서 명령을 내리면 탑재모듈에서 해당 명령을 수행하는 과정을 GUI 환경의 프로그램으로 모니터링 하여 검증하였다. 본 연구를 통하여 국제우주정거장과 탑재모듈 간의 요구사항 분석, 데이터 인터페이스 포맷 정의, 데이터 인터페이스 하드웨어 환경 구현 등의 성과가 있었으며, 추후 탑재모듈 특성이나 국제우주정거장의 구체적인 기능 추가에 의해 탑재모듈 개발을 위한 ETB로 활용할 수 있을 것으로 기대된다.

• Proceedings of the KSRS Conference
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• v.1
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• pp.271-273
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• 2006

In this paper, we describe the MI2U ORB function which is a part of the flight software executed on SCU and controls MI2U/MI which is one of three payloads on COMS. The MI2U ORB function manages MI2U/MI redundancy and reconfiguration, monitors MI2U/MI equipment, performs FDIR, and provides the routing service of commands from Ground/IP (Interpreted Program) through the current used 1553 channel. The MI2U hardware achieves the interface between the SCU and the MI. The MI2U is connected to SCU through MIL-STD-1553B system bus. The MI2U has the internal redundancy but is used in cold redundancy. The MI2U ORB function considers that they are not expected to be simultaneously switched on. The connection combination between MI2U and MI is electrically cross-strapped. However the MI2U ORB function considers only two combinations (MI2U A + MI 1, MI2U B + MI 2). Other combinations can be manually achieved by ground in case of the emergency case.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.188-194
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• 2006

This paper deals with the development of Engineering Model for the TCU( Thruster Control Unit) and simulation system of the reaction control system using cold gas. TCU communicates with TLM(Telemetry) and ground control console so that it transmits monitoring data of pressures and temperatures for reaction control system. The cpu/communication board performs MIL-STD-1553B communication, RS-422 communication, data input/output processing and program loading to EEPROM. We applied Intel 80386DX Microprocessor, 256Kbytes EEPROM and 256Kbytes SRAM for program storage and execution. Also, we developed the direct access interface circuit to EEPROM and simulation system for TCU.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.23 no.4
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• pp.35-40
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• 2023

For the EMC test, the radiation characteristics and immunity characteristics of the EUT are measured under the condition that the EUT maintains its normal operation. For normal operation of the EUT, it is necessary to operate the EUT and monitor its status through separate equipment outside the anechoic chamber. External equipment operates and monitors the EUT through various communications such as 1553B communication, RS-485 communication, and Ethernet communication. At this time, external equipment can transmit noise through the communication line. This noise is transmitted to the LISN through the connected power cable and measured. It is also radiated through the connection terminal to the LISN. In this case, the communication line is the power line It should be designed so that noise is not transmitted through electromagnetic isolation as much as possible. In addition, noise from external equipment must be suppressed as much as possible from entering the chamber through the communication line. In this paper, external EUT test equipment applied for EMC test It explains the considerations in the design and manufacture of the design and explains the satisfaction of the design through tests including CE and RE.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.49-49
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• 2004

국제우주정거장의 데이터 인터페이스를 위하여 항공우주연구원에서는 국제우주정거장에 부착되는 탑재모듈과 국제우주정거장 사이의 데이터 인터페이스에 대한 요구사항을 분석하고 시뮬레이터를 개발하였다. 본 논문에서는 실제 시스템에 직접 이용할 수 있는 특징이 있는 데이터 인터페이스 시뮬레이터의 개발에 대하여 설명한다. 전체 시스템은 두 대의 PC로 구성되어 있으며, 각 PC 시스템은 통신 위해 저속의 1553B 카드와 고속의 FDDI 카드가 설치된다. (중략)

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.274-277
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• 2004

KSLV (Korea Space Launch Vehicle)-I telemetry system will be composed of two telemetry streams: a lower stage telemetry stream and an upper stage telemetry stream. In this paper, the authors present design, implementation and test results of the upper stage telemetry interface for KSLV-I. The telemetry system currently is in the stage of the prototype model development, and its engineering model and flight model will be developed in the near future.

• Proceedings of the KIEE Conference
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• 2002.07d
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• pp.2082-2085
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• 2002

This paper describes the development of a gas turbine engine simulator in detail. The simulator presented in this paper has a mathematical engine model based on a target gas turbine engine performance data and is developed for generating a gas turbine engine sensor signals between the hardwares and softwares of a gas turbine engine control system using Data Acquisition systems(DAS) and 1553B communication, a aeronautic standard communication specification. In addition, this paper proves the excellent performance of this simulator by showing the results of a gas turbine engine field test and simulation.

• Journal of Satellite, Information and Communications
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• v.8 no.1
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• pp.54-60
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• 2013

The need for high performance of on-board computer (OBC) is essential due to the growing requirements and diversified missions, and so OBC has been developed on the basis of the standard design and reconfigurable modularization in order to improve the utilization of OBC for different missions. The processor in OBC of next generation satellite which is currently developed by KARI is adopted the LEON2-FT/AT697F processor based SPARC v8 as main processor and controls various devices such as SpaceWire, MIL-STD-1553B and CAN through PCI on the standardized communication chips. This paper presents the architecture and design of system software for LEON2-FT processor based on PCI, and development of PCI software component. Also it describes the porting of VxWorks 6.5 for LEON2-FT and the test under the simulation environment for LEON2-FT and PCI with communication chips.

• Journal of Advanced Navigation Technology
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• v.27 no.2
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• pp.167-172
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• 2023

The P-3C maritime patrol aircraft operated by the Republic of Korea Navy is equipped with various sensor devices (LRUs, line replace units) for tactical data collection. Depending on the characteristics of the sensor device, it operates with various communication protocols such as IEEE 802.3, MIL-STD-1553A/B, and ARINC-429. In addition, the collected tactical data is processed in the tactical station for mission operators, and this tactical station constitutes a clustering network on Gigabit Ethernet and operates in a distributed processing method. For communication with the sensor device, a specific tactical station mounts a peripheral device (eg. ARINC-429 interface card). The problem is that the performance of the entire distributed processing according to the peripheral device control and communication relay of this specific device is degraded, and even the operation stop of the tactical station has a problem of disconnecting the communication with the related sensor device. In this paper, we propose a method to mount a separate gateway to solve this problem, and the validity of the proposed application is demonstrated through the operation result of this gateway.

• Journal of Aerospace System Engineering
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• v.16 no.1
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• pp.1-11
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• 2022

Avionics Full-DupleX Ethernet (AFDX) is a next-generation avionics network interface technology that is widely applied in the latest aircraft to replace ARINC429 and MIL-STD-1553B. However, the criteria for authenticating an avionics network consisting of AFDX are very scarce. Using AFDX Protocol Analyzer developed by the Korea Electronics Technology Research Institute and AFDX Tap developed by the Korea Aerospace University, we proposed a technology of certification practicality that can verify the normal functioning of avionics equipment with AFDX network interface. Our proposed technology provided the ability to collect precision packets, to verify AFDX specification compliance, and perform automatic tests to reduce the time and cost of authentication of AFDX avionics devices.