• Title/Summary/Keyword: Mission computer

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A Study on System for Synchronization of Multiple UAVs and Ground Control System (무인이동체 및 지상국 컴퓨터 간의 시간 정보 동기화를 위한 시스템 연구)

  • Lee, Won-Seok;Lee, Woon-Sang;Song, Hyoung-Kyu
    • Journal of the Semiconductor & Display Technology
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    • v.19 no.1
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    • pp.11-16
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    • 2020
  • In this paper, system that includes multiple unmanned aerial vehicles (UAVs) are considered. The vehicles are equipped with a mission computer for a specific mission and equipment. The mission equipment operates based on the time of mission computer. Also, data collected by flight computer and mission computer is saved with the time of each operating system. Generally, time offset between multiple computers always exists, though the computers are connected to the Internet. When the data collected by multiple computers is combined, the time offset causes damage on reliability of the combined data. Computers that connected to the Internet are synchronized by network time protocol (NTP). This paper proposes a system that the time of multiple mission computers are synchronized by the same NTP server to minimize the time offset. In the results of the measurement, the system time offset of multiple mission computer is maintained within 10ms from the system time of the server computer.

Design on Flight-Critical Function of Mission Computer for KUH (한국형기동헬기 임무컴퓨터 비행필수기능 설계)

  • Yu, Yeon-Woon;Kim, Tae-Yeol;Jang, Won-Hong;Kim, Sung-Woo;Lim, Jong-Bong
    • Journal of the Korea Institute of Military Science and Technology
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    • v.14 no.2
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    • pp.213-221
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    • 2011
  • Avionics system tends to be designed to have the integrated architecture, and it is getting difficult and complex to verify the flight-critical function because of sophisticated structure. In Korean Utility Helicopter, mission computer acts as the MUX Bus Controller to handle the data from both communication, identification, mission/display and survivability equipment inside Mission Equipment Package and aircraft subsystems such as fuel system and electrical system while it is interfacing with Automatic Flight Control System and Full-Authority Digital Engine Control via ARINC-429 bus. The Flight Displays which is classified as flight-critical function in aircraft is implemented on Primary Flight Display after mission computer processes data from AFCS in order to generate graphics. This paper defines the flight-critical function implemented in mission computer for KUH, and presents the static and dynamic test procedures which is performed on System Integration Laboratory along with Playback Recorder prior to flight test.

A Study on Implementation of a Mission Computer based on COTS (상용 기성품 기반 항공기 임무컴퓨터 구현에 관한 연구)

  • Yang, Sung-Wook;Yang, Jun-Mo;Lee, Sang-Chul
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.22 no.4
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    • pp.81-86
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    • 2014
  • In the development of an avionics system, there is a trend of using commercial-off-the-shelf(COTS) equipments in order to reduce the development cost and time. In this paper, we present an implementation of an aircraft mission computer using the objected oriented software and the COTS equipments. We execute the aircraft guidance software on the system, and measure the calculation time and the used memory. To compare the guidance capability of the software program, we implement the same software logic on DS1104 system. The guidance software program executed on two different systems resulted in the almost identical simulation.

A Study on Performance Comparison of COTS Operating Systems for a Mission Computer Using UAV Collision Avoidance Algorithm (무인기 충돌회피 알고리즘을 이용한 임무컴퓨터용 상용기성품 운영체계 성능 비교에 대한 연구)

  • Yang, Jun-Mo;Jeon, Yu-Ji;Lee, Sang-Chul
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.24 no.4
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    • pp.6-11
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    • 2016
  • There has been an increase in the number of researches on the segment for commercialization after developing avionics systems. In this paper, we have applied a commercial off-the-shelf(COTS) operating systems in an aircraft mission computer. We used UAV collision avoidance algorithms to compare the performance of COTS operating systems. The UAV collision avoidance algorithms were tested on different operating systems to compare the performances of the operating systems. The measured parameters are memory usage and processing time. We have verified that the UAV collision avoidance algorithms worked successfully and compared the performance of each operating system.

A Study of Performance Advanced Technique of the OFP on Multi-Core (멀티 코어 기반의 OFP 성능 향상 기법 연구)

  • Jang, Hyun-Seok;Won, Hyeon-Kwon;Kim, In-Gyu;Ha, Seok-Wun
    • Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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    • pp.270-273
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    • 2012
  • In this paper, I present the design of Operational Flight Programs(OFPs) on a Multi-Core based Mission Computer(MC) for the optimized performance of the OFPs on Multi-Core based MC. The program assigned as tasks on Multi-Core environment can be scheduled by designing with the use of OpenMp, which is the standard for parallel programming. This paper also describes the differences between Multi-Core Program(MCP) on the technique and Single-Core Program(SCP) in terms of performance aspect. The new proposed design technique is applied to the Integrated Up-Front Control OFP(IUFC OFP) on General Processor Module where Multi-Core based. This paper describes the Multi-Core design technique for the optimized performance of the IUFC OFP, which display and control flight data(Navigation, Communication, Identification Friend or Foe) to pilot.

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Implementation and Performance Analysis of High-availability System for Mission Computer (임무컴퓨터를 위한 고가용 시스템의 구현 및 성능분석)

  • Jeong, Jae-Yeop;Park, Seong-Jong;Lim, Jae-Seok;Lee, Cheol-Hoon
    • 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.

Design and Implementation of Multi-Function Display Operational Flight Program and Middleware Using Real-Time and Embedded System Java Virtual Machine (실시간 임베디드 시스템용 자바 가상머신을 이용한 다기능 시현 비행운용 프로그램 및 미들웨어 설계 및 구현)

  • Won, Hyeon-Kwon;Jeong, Chai-Hun;Choi, Kyong-Sik;Kim, Jong-Pil;Kim, In-Gyu
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.39 no.11
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    • pp.1060-1068
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    • 2011
  • In this paper, we present a development of an Operation Flight Program(OFP) on Real Time Operating System(RTOS) and Java Virtual Machine(JVM) of real-time and embedded system. The OFPs are consisted of Multi Function Display(MFD), Integrated Up Front Control(IUFC), Head Up Display(HUD) and Fire Control(FC) and loaded for localization Mission Computer(MC). This paper describes the structure and implementation of a MFD OFP and middleware based on Java.

Safety Design and Validation of Mission Equipment Package for Korean Utility Helicopter (KUH 임무탑재시스템의 안전성설계 및 검증)

  • Kim, Yoo-Kyung;Kim, Myung-Chin;Kim, Tae-Hyun;Yim, Jong-Bong
    • 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.

Development of Message Oriented Middleware for Operational Flight Program in Avionics (항공전자 비행운영프로그램을 위한 메시지 기반 미들웨어 개발)

  • Kim, Jong-Moon;Kim, Ki-Il
    • Journal of the Korea Institute of Information and Communication Engineering
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    • v.20 no.2
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    • pp.299-305
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    • 2016
  • It is require to design the next generation avionics system while considering applicability under open architecture where standerd communication module is used. In this situation, if the existing schemes cannot guarantee new requirement, new system development is demanded. In this paper, we present design, implementation, and testing procedure for message based middleware to support operational flight program on avionics. System architecture include mission computer (MC) and large area display (LAD) over standard socket communication based on reliable Ethernet. Finally, experimental results demonstrate that the proposed middleware can guarantee real-time with 20msec as well as reliability requirements with no lost packet.

Development of Feedback Data Automated Verification Program for Mission S/W (임무 S/W 시험을 위한 피드백 데이터의 기댓값 검증 자동화 도구 개발)

  • Kwon, GI-Bong;Lee, Ha-Yoeun;Ha, Seok-Wun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.10
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    • pp.871-877
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    • 2021
  • Aircraft defects are important matters directly related to the operation of the aircraft and the life of the pilot. The defects in the mission software that occur during aircraft control seriously affect the pilot's mission performance and safety. Therefore, the organization in charge of aircraft development or software defects are reinforced in the process to identify and eliminate defects in the early stages of development, and a lot of labor and time are spent, but due to the nature of the mission software, strong functional coupling with other avionics and high complexity, so there are restrictions on the identification and removal of software defects through the existing test method. This study analyzes the effect of securing mission software integrity and reducing test cost through data integrity verification by developing a tool that automates the verification of expected value of feedback data among communication data of mission computer interlocking equipment.