• 제목/요약/키워드: Aircraft System Integration

검색결과 97건 처리시간 0.021초

항공기 부품 스마트 공장 구축 프로세스 연구 (A Study on Design and Implementation Processes of a Smart Factory for Aircraft Parts)

  • 김병주;김덕현;이인수;전차수
    • 대한산업공학회지
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    • 제43권3호
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    • pp.229-237
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    • 2017
  • Presented in this paper is a case study of constructing a smart factory for aircraft parts. The construction procedure involves four phases. First of all, its management goals are set, and layout design and simulation are carried out in the conceptual design phase. In the detail design phase, operating scenarios for each module are written out, and probable risks are analyzed by expert groups, and then requirements for developing equipments and subsystems are determined with consideration for element technologies and their integration schemes into the smart factory. In the fabrication and installation phase, system development, equipment fabrication and installation are proceeded in a separate manner, and then integrated together subsequently. In the operation and improvement phase, the factory is stabilized, sophisticated and improved constantly during real operation.

RDS(Robotic Drilling System) 구축을 위한 전용 End-Effector Prototype 개발에 관한 연구 (A Study on the Development of a Specialized Prototype End-Effector for RDSs(Robotic Drilling Systems))

  • 김태화;권순재
    • 한국기계가공학회지
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    • 제12권6호
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    • pp.132-141
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    • 2013
  • Robotic Drilling Systems(RDSs) set the standard for the factory automation systems in aerospace manufacturing. With the benefits of cost effective drilling and predictive maintenance, RDSs can provide greater flexibility in the manufacturing process. The system can be easily adopted to manage very complex and time-consuming processes, such as automated fastening hole drilling processes of large aircraft sections, where it would be difficult accomplished by workers following teaching or conventional guided methods. However, in order to build an RDS based on a CAD model, the precise calibration of the Tool Center Point(TCP) must be performed in order to define the relationships between the fastening-hole target and the End Effector(EEF). Based on the kinematics principle, the robot manipulator requires a new method to correct the 3D errors between the CAD model of the reference coordinate system and the actual measurements. The system can be called as a successful system if following conditions can be met; a. seamless integration of the industrial robot controller and the IO Level communication, b. performing pre-defined drilling procedures automatically. This study focuses on implementing a new technology called iGPS into the fastening-hole-drilling process, which is a critical process in aircraft manufacturing. The proposed system exhibits better than 100-micron 3D accuracy under the predefined working space. Based on the proposed EEF fastening-hole machining process, the corresponding processes and programs are developed, and its feasibility is studied.

초연결 시대의 UAS 주파수의 효율적 활용방안 (An Efficient Frequency Utilization Policy for UAS in Hyper-Connectivity Era)

  • 강영흥
    • 한국전자파학회논문지
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    • 제26권10호
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    • pp.914-923
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    • 2015
  • UAS(Unmanned Aircraft System)는 과거 군용으로 국한되어 활용되었으나, 최근 기술발전에 힘입어 점차 민간용 시장으로 확대되고 있으며, 그 시장 규모가 급격히 성장할 것으로 예상된다. 특히 초연결 시대의 UAS의 이용 형태는 넥스트(next) 5G 시스템 아키텍처에서 하나의 가능한 기반시설로 큰 역할을 할 것이다. UAS에서의 궁극적인 목표는 국가 공역 시스템(NAS: National Airspace System)으로의 통합 운용이며, 이를 위해 무인 비행체 제어를 위한 비업무용(non-payload) 주파수뿐만 아니라, 초연결시대의 다양한 활용분야에 필요한 업무용(payload) 주파수 확보가 중요한 요소이다. 이에 본 연구에서는 기존의 UAS 무선조정용 주파수의 분석과 비업무용 주파수 개발 연구동향 및 향후 UAS 주파수의 효율적 활용방안을 제안한다.

위성체용 2비트 오류검출 및 1비트 정정 FPGA 구현 (A SEC-DED Implementation Using FPGA for the Satellite System)

  • 노영환;이상용
    • 제어로봇시스템학회논문지
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    • 제6권2호
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    • pp.228-233
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    • 2000
  • It is common to apply the technology of FPGA (Fie이 Programmable Gate Array) which is one of the design methods for ASIC(Application Specific IC)to the active components used in the data processing at the digital system of satellite aircraft missile etc for compact lightness and integration of Printed Circuit Board (PCB) In carrying out the digital data processing the FPGAs are designed for the various functions of the Process Control Interrupt Control Clock Generation Error Detection and Correction (EDAC) as the individual module. In this paper an FPGA chip for Single Error Correction and Double Error Detection (SEC-DED) for EDAC is designed and simulated by using a VLSI design software LODECAP.

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항공전자 시스템 통합을 위한 데이터 버스 연구 (A Study on the Data Bus for the Integration of Avionics Systems)

  • 홍승범;지민석;김영인;홍교영;천기진
    • 한국항공운항학회지
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    • 제17권3호
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    • pp.70-77
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    • 2009
  • We proposed the method of avionics integrated architecture using high-speed fiber optic bus. Typically, data bus of aircraft consists of electronic and optic data transmission method. Avionics systems are difficult to operate the electronic data transmission method for the high speed data processing, synchronization and interconnection between flight control system and flight management system efficiently. In this paper, it is known to look into the problem of data bus and the advanced trend in avionics systems, and propose the appropriate data bus of the advanced avionics systems.

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생존체계 위협조우 상황인지를 위한 복합/다중 위협상황 Emulation 연구 (A Study on Complex Threat Emulation for Situation Awareness of ASE System)

  • 이문석;이정원
    • 한국정보통신학회논문지
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    • 제14권10호
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    • pp.2180-2186
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    • 2010
  • 무기체계의 현대화 및 복잡화에 따라 현대전 상황에서의 플랫폼 및 운용자에 대한 생존성 확보를 필요로 하게 되었다. 현대 전장의 복합 및 다중 위협상황 무기체계에 대응하기 위하여 다수의 무기체계 플랫폼에서 생존체계를 함께 탑재하게 된다. 생존체계는 무기체계 플랫폼을 위협하는 위협들을 탐지/식별하며 효율적인 대응을 통하여 운용자로 하여금 정확한 상황인지를 가능하게 하고 플랫폼의 생존 능력을 향상시킨다. 생존체계가 보유하여야 할 중요 성능 인자는 복합 및 다중 위협에 대한 처리를 통하여 생존성을 확보하는 것이다. 이에 본 논문에서는 레이다, 레이저, 미사일 단일 위협상황을 조합한 복합 위협상황을 다룸으로 하여 생존체계가 보유하여야 하는 위협통합 알고리즘을 제시하고, 복합 위협상황을 Emulation하는 시스템을 실험실 환경에서 구현하여 위협통합 알고리즘에 대한 성능을 검증하였다. 이를 통해 생존체계가 플랫폼 탑재 이전에 성능 및 신뢰성을 확보할 수 있는 방안에 대하여 제시한다.

데이터 중심 통합생산시스템 설계 및 구현: 대형항공부품가공 사례 (Design and Implementation of Integrated Production System for Large Aviation Parts)

  • 배성문;배효진;홍금석;박철순
    • 산업경영시스템학회지
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    • 제44권4호
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    • pp.208-219
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    • 2021
  • In the era of the 4th industrial revolution driven by the convergence of ICT(information and communication technology) and manufacturing, research on smart factories is being actively conducted. In particular, the manufacturing industry prefers smart factories that autonomously connect and analyze data. For the efficient implementation of smart factories, it is essential to have an integrated production system that vertically integrates separately operated production equipment and heterogeneous S/W systems such as ERP, MES. In addition, it is necessary to double-verify production data by using automatic data collection technology so that the production process can be traced transparently. In this study, we want to show a case of data-centered integration of a large aircraft parts processing factory that requires high precision, takes a long time, and has the characteristics of processing large raw materials. For this, the components of the data-oriented integrated production system were identified and the connection structure between them was explained. And we would like to share the experience gained through the design and implementation case. The integrated production system proposed in this study integrates internal components based on data, which is expected to serve as a basis for SMEs to develop into an advanced stage, and traces materials with RFID technology.

Attitude Determination GPS/INS Integrated Navigation System with FDI Algorithm for a UAV

  • Oh Sang Heon;Hwang Dong-Hwan;Park Chansik;Lee Sang Jeong;Kim Se Hwan
    • Journal of Mechanical Science and Technology
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    • 제19권8호
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    • pp.1529-1543
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    • 2005
  • Recently an unmanned aerial vehicle (UAV) has been widely used for military and civil applications. The role of a navigation system in the UAV is to provide navigation data to the flight control computer (FCC) for guidance and control. Since performance of the FCC is highly reliant on the navigation data, a fault in the navigation system may lead to a disastrous failure of the whole UAV. Therefore, the navigation system should possess a fault detection and isolation (FDI) algorithm. This paper proposes an attitude determination GPS/INS integrated navigation system with an FDI algorithm for a UAV. Hardware for the proposed navigation system has been developed. The developed hardware comprises a commercial inertial measurement unit (IMU) and the integrated navigation package (INP) which includes an attitude determination GPS (ADGPS) receiver and a navigation computer unit (NCU). The navigation algorithm was implemented in a real-time operating system with a multi-tasking structure. To evaluate performance of the proposed navigation system, a flight test has been performed using a small aircraft. The test results show that the proposed navigation system can give accurate navigation results even in a high dynamic environment.

The Dynamics of Noise and Vibration Engineering Vibrant as ever, for years to come

  • Leuridan, Jan
    • 한국소음진동공학회:학술대회논문집
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    • 한국소음진동공학회 2010년도 춘계학술대회 논문집
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    • pp.47-47
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    • 2010
  • Over the past 20 years, constant progress in noise and vibration (NVH) engineering has enabled to constantly advance quality and comfort of operation and use of really any products - from automobiles to aircraft, to all kinds of industrial vehicles and machines - to the extend that for many products, supreme NVH performance has becomes part of its brand image in the market. At the same time, the product innovation agenda in the automotive, aircraft and really many other industries, has been extended very much in recent years by meeting ever more strict environmental regulations. Like in the automotive industry, the drive towards meeting emission and CO2 targets leads to very much accelerated adoption of new powertrain concepts (downsizing of ICE, hybrid-electrical...), and to new vehicle architectures and the application of new materials to reduce weight, which bring new challenges for not only maintaining but further improving NVH performance. This drives for innovation in NVH engineering, so as to succeed in meeting a product brand performance for NVH, while as the same time satisfying eco-constraints. Product innovation has also become increasingly dependent on the adoption of electronics and software, which drives for new solutions for NVH engineering that can be applied for NVH performance optimization of mechatronic products. Finally, relentless pressure to shorten time to market while maintaining overall product quality and reliability, mandates that the practice and solutions for NVH engineering can be optimally applied in all phases of product development. The presentation will first review the afore trends for product and process innovation, and discuss the challenges they represent for NVH engineering. Next, the presentation discusses new solutions for NVH engineering of products, so as to meet target brand values, while at the same time meeting ever more strict eco constraints, and this within a context of increasing adoption of electronics and controls to drive product innovation. NVH being very much defined by system level performance, these solutions implement the approach of "Model Based System Engineering" to increase the impact of system level analysis for NVH in all phases of product development: - At the Concept Phase, to be able to do business case analysis of new product concepts; to arrive at an optimized and robust product architecture (e.g. to hybrid powertrain lay-out, to optimize fuel economy); to enable target cascading, to subsystem and component level. - In Development Phase, to increase realism and productivity of simulation, so as to frontload virtual validation of components and subsystems and to further reduce reliance on physical testing. - During the final System Testing Phase, to enable subsystem testing by a combination of physical testing and simulation: using simulation models to simulate the final integration context when testing a subsystem, enabling to frontload subsystem testing before final system integration is possible. - To interconnect Mechanical, Electronical and Controls engineering, in all phases of development, by supporting model driven controls engineering (MIL, SIL, HIL). Finally, the presentation reviews examples of how LMS is implementing such new applications for NVH engineering with lead customers in Europe, Asia and US, with demonstrated benefits both in terms of shortening development cycles, and/or enabling a simulation based approach to reduce reliance on physical testing.

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항공전자 시스템 통합시험장비 개발 (Development of Avionics Hot Bench for Avionics System Integration Test)

  • 김진혁;이상철;류광수
    • 한국항공우주학회지
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    • 제36권5호
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    • pp.507-513
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    • 2008
  • 본 논문에서는 비행운용프로그램 검증 및 항공전자 장비 고장탐구에 사용되는 항공전자시스템 통합시험장비(Avionics Hot Bench) 개발에 대한 내용을 기술하였다. 산업분야에서 전통적 AHB는 자사 보유 소프트웨어 및 신뢰성 있는 하드웨어를 오랜 기간 통합하여 개발되며 기술이전에는 일반적으로 큰 비용이 요구된다. 개발 기간과 비용을 절감하기위해 다수의 기성개발품을 활용하였으며, 개방형 시스템 구조를 적용하여 실제 항공전자 시스템 개발에 사용될 수 있는 AHB를 개발하였다. 검증절차서에 입각하여 T-50 항공전자 시스템 개발에 사용된 기 입증된 AHB의 테스트 결과와 개발된 AHB의 테스트 결과를 엄밀히 비교하였으며 만족스러운 비교 결과를 얻을 수 있었다.