• Proceedings of the KIEE Conference
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• 2007.07a
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• pp.1868-1869
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• 2007

항공기의 임무컴퓨터는 외부영상과 비행관련 정보들을 시현하기 위한 그래픽 처리를 담당한다. VIOM은 외부영상신호를 임무컴퓨터의 각 모듈에 전달하고, 내부모듈에서 생성한 비행관련정보들을 원하는 시현장치로 전송하는 역할을 한다. 현재 개발하고자 하는 KHP용 임무컴퓨터의 VIOM은 영상수신처리회로, 영상분배 및 선택회로, 모듈영상수신 및 분배회로, 모듈영상선택회로, 그리고 영상선택 정보를 획득하기 위한 데이터 인터페이스 등으로 구성된다. 본 논문은 KHP 임무컴퓨터 VIOM 의 전체 인터페이스 구성과 이를 위한 각 회로 설계에 대한 정보를 제시함을 목적으로 한다.

• The KIPS Transactions:PartA
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• v.16A no.4
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• pp.235-244
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• 2009

The mission-critical computer for air defense has to maintain its operation without any fault for a long mission time and is required to implement at low cost. Now the reliability of the mission critical-computer using Active Sparing Redundancy fault-tolerant technique is inferior to that of the computer using TMR technique. So in this paper are proposed Extended ASR(EASR) technique that provides higher reliability than that of the computer using TMR technique. The fault-tolerant performance of the implemented mission-critical computer is proven through reliability analysis and numbers of fault recovery test. Also, the reliability of the mission-critical computer using EASR technique is compared with those of computer using ASR and TMR techniques. EASR technique is very suitable to the mission-critical computer.

• The KIPS Transactions:PartA
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• v.15A no.6
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• pp.309-316
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• 2008

The mission-critical engagement control computer for air defense has to maintain its operation without any fault for a long mission time. The mission performed by large-scale and complex embedded software is extremely critical in terms of dependability and safety of computer system, and it is very important that engagement control computer has high reliability. The engagement control computer was implemented using four processors. The distributed computer composed of four processors quarantees the dependability and safety, and ASR fault-tolerant technique applied to each processor guarantees the reliability. In this paper, the mechanism and performance of ASR fault-tolerant technique are analysed. And MTBF, reliability, availability, and cost-effectiveness for ASR, DMR and TMR techniques applied to the engagement control computer are analysed. The mission-critical engagement control computer using software-based ASR fault-tolerant technique provides high reliability and fast recovery time at a low cost. The mission reliability of the engagement control computer using ASR technique in 4 processors board is almost same the reliability of the computer using TMR technique in 6 processors board. ASR technique is most suitable to the mission-critical engagement control computer.

• Proceedings of the Korea Information Processing Society Conference
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• 2009.04a
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• pp.688-691
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• 2009

항공기에는 각각의 임무에 맞게 설계된 많은 종류의 임무컴퓨터(Mission Computer)가 존재한다. 여러 센서(Sensor)에서 전송되는 신호를 처리하는 기존의 단일코어 기반 임무컴퓨터는 항공기의 성능 향상에 따른 임무 요구도의 증대와 전장 환경의 변화에 따라 기내 데이터의 양이 급격히 증가하여 정보통신의 실시간성에 한계를 보인다. 본 논문에서는 실시간 운영체제인 VxWorks를 통해서 다중채널 ARINC-429 통신모듈을 실시간으로 제어하는 멀티코어 SBC(Single Board Computer) 테스트베드(Test-Bed)를 제시한다.

• Proceedings of the Korean Information Science Society Conference
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• 2010.06b
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• pp.425-430
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• 2010

항공기 내에서 단일코어 기반의 임무컴퓨터를 포함하는 연합형 항공전자 모델은 항공기의 임무 요구도 증대와 전장 환경의 변화에 따라 기내 데이터 양이 급격히 증가하여 비행 운용 프로그램(OFP)의 실시간성 및 처리성능에 한계를 보인다. 또한 분산된 임무컴퓨터의 공간점유와 무게 및 높은 전력소비가 발생하므로, 본 연구에서는 실시간 운영체제 모듈을 적용한 멀티코어 기반의 통합 모듈형 시스템(IMA) 플랫폼을 제시하여 비용과 체적을 감소시킨 개발 환경을 제공한다.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.54-54
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• 2004

과학기술위성 1호는 2003년 9월에 발사 후 초기 운용 단계를 거쳐 현재 정상적인 임무수행 단계이다. 위성의 주 컴퓨터 시스템은 각 탑재체들이 임무를 원활히 수행하도록 위성의 건강 상태를 감시하고, 시나리오에 따라 각 탐재체들을 제어하고, 각종 위성 관측 자료를 수집하며, 위성의 임무 수행을 위한 명령을 송수신 한다. 본 발표에서는 지난 6개월간 위성의 운용을 위하여 지상으로부터 명령을 수신하고, 수신된 명령을 동작순서에 따라 각 서브시스템에 전달하는 위성의 주 컴퓨터 운용과 관련하여 운용현황을 살펴본다. (중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.8
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• pp.813-822
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• 2010

Integrated data processing for display of flight critical data and mission critical data was conducted without additional display instruments using glass cockpit design. Based on a pre-designed flight critical system and a mission critical system, this paper shows an optimal design of subsystem integration. The design satisfies safety requirements of flight control systems(FCS) and requires minimized modification of pre-designed systems. By conducting integration test using System Integration laboratory(SIL), it is confirmed that the introduced design approach meets the safety requirements of the MEP system.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.22 no.2
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• pp.354-361
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• 2018

This paper describe the Lateral Navigation algorithm design and verification that implementation on Mission Computer's OFP for Korean Utility Helicopter(KUH) instead of Auto Flight Control System(AFCS) Vehicle Management System. The LNAV function transmits Roll command into the AFCS System. The Roll command value will be calculated by control algorithms in MC. The Operational Flight Program(OFP) shall use for its calculations different measurements of the aircraft's attitude and place. Using these inputs, the OFP will translate a navigational demand(for example-to perform the selected flight plan) into Roll commands to the autopilot. By conducting integration test using SIL and ground test, flight test, it is confirmed that the introduced algorithm meets the requirements of the Mission Equipment Package(MEP) system. LNAV function is verified through the System Integration Laboratory(SIL) test, ground and flight test.

• Proceedings of the Korea Contents Association Conference
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• 2008.05a
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• pp.529-533
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• 2008

Mission Computer performs important role both managing a whole system and dealing with a specific mission in avionics system. In general, the fault of SPOF(Single Point Of Failure) in unity system can lead to failure of whole system. It can cause a failure of a mission and also can threaten to the life of the pilot. So, in this paper, we design the HA(High-availability) system so that dealing with the failure. And we use HA software like Heartbeat, Fake, DRBD and Bonding to managing HA system.

• The Journal of the Korea Contents Association
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• v.8 no.8
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• pp.47-56
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• 2008

MC(Mission Computer) performs important function in avionics system which tactic data processing, image processing and managing navigation system etc. In general, the fault of SPOF(Single Point Of Failure) in unity system can lead to failure of whole system. It can cause a failure of a mission and also can threaten to the life of the pilot. So, in this paper, we design the HA(Hight-availability) system so that dealing with the failure. And we use HA software like Heartbeat, Fake, DRBD and Bonding to manage HA system. Also we analyze the performance of HA system using the FDT(Fault Detection Time) for fast fault detection and MTTR(Mean Time To Repair) for mission continuity.