• Title/Summary/Keyword: 헬리콥터 설계

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A Study on the Development of Flight Simulator Training Device for the Prevention of Helicopter Flight Spatial Disorientation (헬리콥터 비행착각 예방을 위한 모의비행훈련장치 개발에 대한 연구)

  • Se-Hoon Yim
    • Journal of Advanced Navigation Technology
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    • v.27 no.2
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    • pp.155-161
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    • 2023
  • Vertigo refers to a state in which awareness related to the location, posture, movement, etc. of a helicopter is insufficient in space. It is easy to fall into flight illusion when flying in dense fog or night flight, and even if it has a wide field of view, it can be caused by visual causes such as cloud shapes, wind conditions, conditions of ground objects, and sensory causes such as changes in air posture or gravitational acceleration. The design and program of the motion system are studied that applied a six-axis motion system to a conventional commercial flight simulator program for pilot training, depending on the specificity of helicopter flight training that requires perception and sensitivity. Using the motion-based helicopter simulator produced in this study to train pilots, it is expected to have a positive effect in prevent of vertigo, where high performance could not be confirmed in the previously used visual-based simulation training device.

Design and Analysis of Flexbeam in SNUF Blade Equipped with Active Trailing-Edge Flap for Helicopter Vibratory Load Reduction (헬리콥터 진동 하중 저감을 위한 능동 뒷전 플랩이 장착된 SNUF 블레이드의 유연보의 설계 및 해석)

  • Im, Byeong-Uk;Eun, Won-Jong;Shin, SangJoon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.46 no.7
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    • pp.542-550
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    • 2018
  • This paper presents design of a bearingless main rotor of SNUF (Seoul National University Flap) blade equipped with active trailing-edge flap to reduce the hub vibratory loads during helicopter forward flight. For that purpose, sectional design of the flexbeam is carried out using the thin-walled composite material rotating beam vibration analysis program (CORBA77_MEMB) in EDISON. Using the multi-body dynamics analysis program, DYMORE, blade dynamic characteristics and those of the loads control are examined using the active trailing-edge flap in terms of the flexbeam sectional design.

Aerodynamic Design of Helicopter Rotor Airfoil in Forward Flight Using Response Surface Method (반응표면법을 이용한 전진비행하는 헬리콥터 로터 에어포일의 공력설계)

  • Sun, Hyo-Sung;Lee, Soo-Gab
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.7
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    • pp.13-18
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    • 2004
  • This paper describes an efficient and robust optimization method for helicopter rotor airfoil design in forward flight. Navier-Stokes analysis was employed to compute the dynamic response of an airfoil, which simulates the unsteady rotor flow-field in forward flight. The optimization system consists of two categories; Response Surface Method to construct the response surface model based on D-optimal 3-level factorial design, and Genetic Algorithm to obtain the optimum solution of a defined objective function including penalty terms of constraints. The influence of design variables and their interactions on the aerodynamic performance was examined through the optimization process.

DESIGN-ORIENTED AERODYNAMIC ANALYSES OF HELICOPTER ROTOR IN HOVER (정지비행 헬리콥터 로터의 설계를 위한 공력해석)

  • Jung H.J.;Kim T.S.;Son C.H.;Joh C.Y.
    • Journal of computational fluids engineering
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    • v.11 no.3 s.34
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    • pp.1-7
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    • 2006
  • Euler and Navier-Stokes flow analyses for helicopter rotor in hover were performed as low and high fidelity analysis models respectively for the future multidisciplinary design optimization(MDO). These design-oriented analyses possess several attributes such as variable complexity, sensitivity-computation capability and modularity which analysis models involved in MDO are recommended to provide with. To realize PC-based analyses for both fidelity models, reduction of flow domain was made by appling farfield boundary condition based on 3-dimensional point sink with simple momentum theory and also periodic boundary condition in the azimuthal direction. Correlations of thrust, torque and their sensitivities between low and high complexity models were tried to evaluate the applicability of these analysis models in MDO process. It was found that the low-fidelity Euler analysis model predicted inaccurate sensitivity derivatives at relatively high angle of attack.

A Design of Augmented Reality Interface for Helicopter Navigation (헬리콥터 항법을 위한 증강현실 인터페이스 설계)

  • 이헌주;변기종;박찬용;김주완;장병태
    • Proceedings of the Korean Society for Emotion and Sensibility Conference
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    • 2000.11a
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    • pp.217-221
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    • 2000
  • 증강현실은 사용자가 보고 있는 실세계의 영상과 컴퓨터가 생성한 가상의 영상을 실시간으로 합성하여 제시해주는 기술로 사용자에게 실세계에 대한 이해 및 현실감을 높여 줄 수 있는 기술이다. 본 논문에서는 이러한 기술을 이용하여 조종사에게 항법관련 정보를 제공해줄 수 있는 헬리콥터 항법용 증강현실 인터페이스를 설계하는 것을 목적으로 한다. 증강현실 인터페이스는 위치 측위를 위한 GPS/INS 기술과 통합되어 조종사에게 실시간으로 항법관련 정보를 제공해줄 수 있도록 한다. 제안된 시스템에서는 조종사의 주시방향을 보다 정확하게 추출하기 위하여 레이저 방식의 트래커를 이용하며, 투시형 HMD(Head-mounted Display)를 이용하여 합성된 영상을 조종사에게 실시간으로 제공하도록 한다.

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Performance Analysis and Preliminary Design for the Turbo-Shaft Engine of the Multi-Purpose Helicopter (다목적 쌍발 헬리콥터용 터보축 엔진의 성능해석 및 기본설계)

  • Seo, Jeong-Won;Yun, Geon-Sik
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.26 no.1
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    • pp.55-65
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    • 2002
  • In this study, the procedures for the preliminary design of the turbo-shaft engine for the light multi-purpose helicopter are established. The engine specifications are determined through the performance analysis on the on-design and off-design conditions by the use of simulation program. In addition, the effect of humidity on the engine performance is examined by considering the change of the gas properties and characteristic maps due to moisture contents. The calculation results show that the engine power is reduced by the existence of moisture in working fluid.

Modification of a Two Stage Axial Compressor of a Turboshaft Engine for Helicopters (헬리콥터용 터보샤프트엔진 2단 축류압축기 개량설계)

  • Kim, Jin-Han;Kim, Chun-Taek;Lee, Dae-Sung
    • The KSFM Journal of Fluid Machinery
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    • v.2 no.1 s.2
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    • pp.88-95
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    • 1999
  • This paper introduces the part of efforts to develop a derivative type turboshaft engine from an existing baseline engine for multi-purpose helicopters aiming at 4000 kg of take-off weight for 10-12 passengers. As a first step in meeting the development goal of increasing the output power from 720 hp to 840hp with minimum modification, a two stage axial compressor was redesigned to obtain the higher pressure ratio by removing the inlet guide vane and increasing the chord length. As a result, a two stage axial compressor was designed to facilitate a flow rate of 3.04 kg/s, a pressure ratio of 2.01 and an adiabatic efficiency of $85\%$. Its performance tests were carried out and verification of test results and redesign are under progress. Aerodynamic and structural analyses of the preliminary design are mainly described in this paper.

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A Design of Fire Monitoring System Based On Unmaned Copter and Sensor Network (무인헬기 및 센서네트워크 기반 화재 감시 시스템 설계)

  • Yun, Dong-Yeol;Kim, Seong-Ho
    • Proceedings of the Korean Institute of Intelligent Systems Conference
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    • 2006.11a
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    • pp.383-387
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    • 2006
  • 본 연구에서는 신속하고 정확한 산불감지를 위해 센서 네트워크 기술 및 무인 항공 기술을 접목한 새로운 형태의 화재 감지 시스템을 제안하고자 한다. 제안된 시스템은 광범위한 영역에 설치되는 다수의 센서 노드들과 이 영역위에서 자유로이 비행하면서 실시간으로 센서 노드에서 계측된 데이터를 수집하는 헬리콥터 및 헬리콥터에 장착되어 화재발생지점의 화상정보를 취득하고 이를 원격의 서버로 데이터를 무선 전송할 수 있는 임베디드 시스템으로 구성된다. 또한 산불 감지용 테스트베드를 제작하여 설계 제작된 시스템의 실제 적용을 통해 제안된 시스템의 유용성을 확인하고자 한다.

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