• Journal of the Korea Institute of Military Science and Technology
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• v.9 no.1 s.24
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• pp.89-98
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• 2006

This paper describes signal attenuation characteristics as splicing the output on LVDT for stability and reliability of switching mechanism, which is developed to use common signal between FLCC and EDFLCC, on T-50 aircraft. The method of test is classified a Pspice simulation and an actual hardware evaluation. The difference of error margin for two methods is 10times, the latter higher. The result in this experiment shows that the signal attenuation as splicing the output on LVDT doesn't affect and the static error margin is 53% for develope the EDFLCC.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.2
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• pp.169-179
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• 2010

Satisfying the same probability of loss of control and essentially two fail operative performance with a triplex computer architecture requires a lot of modification of the conventional redundancy management design techniques, previously employed in quadruplex digital flight control computer. T-50 FCS for triplex redundancy management design applied an advanced digital flight control architecture with an I/O controller which is functionally independent of the digital computer to achieve the same reliability and special failure analysis and isolation schemes for fail operational goals with a triplex configuration. The analysis results indicated that the triplex flight control system is to satisfy the safety requirement utilizing the advanced flight control techniques and the system performance of the implemented flight control system was verified by failure mode effect test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.12
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• pp.857-866
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• 2022

Fixed-wing UAVs have long endurance and range capabilities compared to other aerial platforms. These advantages led fixed-wing UAVs to become a popular platform for reconnaissance missions in the military. In this research, we modeled fixed-wing UAVs, including the landing gear model and developed a guidance and control system for flight control computers to construct a HILS environment. We also developed an autopilot system that includes automated take-off, cruise, and landing control for UAVs. We also retrived the Aerodynamic coefficients an UAV using Datcom and AVL software and used them for 6 degrees of freedom modeling. The Flight control computer calculates guidance commands using the Carrot chasing guidance law after distinguishing the condition of the UAV based on 16 pre-defined flight modes and calculates control inputs using Nonlinear Dynamic Inversion (NDI) control scheme. We used RTNngine to integrate the Simulink model and flight control computer for HILS environment formulation.

• Communications of the Korean Institute of Information Scientists and Engineers
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• v.34 no.10
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• pp.19-23
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• 2016

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.940-947
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• 2007

For the performance upgrade of a supersonic jet fighter, the processor and FLCC(Flight Control Computer) Architecture were upgraded from a baseline FLCC. Prior to the hardware implementation phase, the exact CPU throughput estimation is necessary. For this purpose, an experimental method for new FLCC throughput estimation was introduced in this study.　While baseline FLCC operating, the CPU address bus was collected with logic analyzer, and then decoded to get the exact access times to each memory-memory and the number of program Instruction branches. Based on these data, a throughput test in CPU demo-board of the new FLCC configuration was performed. From test results, the CPU-Memory architecture was design-changed before FLCC hardware implementation phase. To check the flight stability degradation due to power-interrupt problem due to CPU-Memory architecture change, the piloted HILS (Hardware-In-the Loop Simulator) test was conducted.

• Proceedings of the Korean Society of Computer Information Conference
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• 2021.01a
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• pp.171-172
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• 2021

현재까지 항공기에 적용되는 기술들은 수많이 발전해왔다. 조종사의 편의성을 위한 기술들 또한 많이 발전해왔다. 자동운항 등 많은 기술들이 조종사를 보조하며 편의성을 위해 사용되고 있다. 하지만 비행기가 처음 만들어 졌을 때부터 바뀌지 않은 조종의 방식과 항공기의 국제성이 가지는 장시간의 비행은 여전히 조종사에게는 큰 피로를 안겨주고 있다. 본 논문은 조종사들의 피로를 경감 시켜 피로로 인해 발생 할 수 있는 사고들을 예방하기 위해 음성인식을 적용하여 새로운 조종의 방식인 '음성인식을 통한 항공기 조종면의 제어' 기술을 제안한다. 기존의 손을 사용한 조종방식이 아닌 컴퓨터와 조종사의 대화를 통해 데이터를 처리하고 즉각적인 피드백을 받으며 조종사의 편의성을 증가시켜 나아가 피로를 경감 시킬 수 있다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2016.10a
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• pp.227-229
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• 2016

Drone is demanding more than detaile hardware and software systems because Drone have characteristic flying. If Drone is a plane crash. they have risk of personal injury and property damage. now Drone control core system is preventing a plane crash and flight unsafe flying. The key is to help flying to convert for various external environment. This research prevent a plane crash that system planning to treat six-senser-figure doubly is IMU trouble or a trouble caused by a passing parameters and IMU install to help stability in flying.

• Proceedings of the Korea Information Processing Society Conference
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• 2009.11a
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• pp.83-84
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• 2009

최근 다양한 센싱장치와 HCI 디바이스를 결합하여 로봇이나 기계장치를 구동하려는 연구가 활발하게 진행되고 있다. 또한 기존의 RC방식의 무인비행체 조작은 관련분야의 전문성을 필요로 할 만큼 접근하기 어려운 면이 있었다. 이에 본 논문에서는 소형 무인비행체(UAV)의 움직임 제어를 위해 데이터 글로브의 손가락 구부러짐을 인식하여 이를 통해 무인비행체를 조작하는 원격조종장치에 관한 시스템 구조 및 프로토콜을 제안한다. 이 시스템을 통해 비전문가로 하여금 무인비행체의 접근성을 높이며 다양한 분야에 활용 할 수 있는 가능성을 제시하고자 한다. 이를 위해 데이터 글로브의 센싱 데이터에 대한 조합 및 해석방식을 정의하고, 이를 데이터 글로브의 손가락 구부러짐 해석에 적용하였다. 또한 조합된 명령신호를 전송하는 무인비행체의 구동 제어를 위한 비동기 Uplink 프로토콜을 제안하였다.

• Proceedings of the Korean Society of Computer Information Conference
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• 2022.01a
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• pp.325-326
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• 2022

최근 무인 항공 기술의 발전과 함께 드론의 상업적 활용이 가속화되고 있다. 산업계 및 학계에서는 인공지능, 사물인터넷 등 지능정보기술을 활용하여 드론 응용에 자율 비행을 적용하고자 노력하고 있지만 해결되지 못한 문제들이 산적해 있다. 그러므로 완전 자율 비행은 아니지만, 드론 조종에 경험이 없는 비전문가도 드론을 용이하게 조정할 수 있는 반자동 방식의 비행 제어를 채택한 드론 응용이 개발이 필요하다. 따라서 본 논문에서는 실내환경에서 정찰 임무 수행을 위한 반자동 비행 조종 시스템을 제안한다. 제안한 시스템은 교차로 지점마다 사용자에게 이동 방향을 선택할 기회를 제공하고 교차로 간 일정한 속도 및 벽면과의 일정한 간격으로 자율비행하도록 제어한다. 또한, 실내 측위 기술인 ORB-SLAM 알고리즘을 이용하여 드론이 실내 공간 및 자신의 위치를 파악하도록 한다.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2012.05a
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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.