• Title, Summary, Keyword: Cyclocopter

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Design and Manufactures of Cyclocopter Composite Wing Blades (사이클로콥터의 복합재료 Wing blade 설계 및 제작)

  • 김승조;윤철용;백병주
    • Proceedings of the Korean Society For Composite Materials Conference
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    • pp.187-190
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    • 2000
  • Cyclocopter is air vehicle to vertically take-off and land like a helicopter. This is an efficient and quiet means of being able to direct thrust compared to a helicopter. The rotor consists of several blades rotating about a horizontal axis perpendicular to the direction of normal flight. The direction of blade span is parallel to rotating axis and both end roots are connected to the hub to resist centrifugal force and to transmit the power. The pitch of the individual blades to the tangent of the circle of the blade's path is varied cyclically to gain thrust. In the paper, the design and manufactures of cyclocopter rotor blades are presented. Stress at the roots of cyclocopter blades is great due to centrifugal and aerodynamic forces and aeroelastic instabilities appear. The blades consist of main spar, front spar, polyurethan foam, weight, and skin and spars and skin are made of glass/epoxy composite.

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Structural Design and Analysis of Composite Cyclocopter Rotor Blades (복합재료 사이클로콥터 로터 블레이드의 구조 설계 및 해석)

  • Hwang In Seong;Hwang Chang Sup;Yun Chul Yong;Kim Seung Jo
    • Proceedings of the Korean Society For Composite Materials Conference
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    • pp.91-94
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    • 2004
  • A cyclocopter with the cycloidal blades system can be the type of UAV which can combine the high-speed characteristics of the conventional airplane with the low-speed characteristics of the helicopter. The cycloidal blades system, which can be described as a horizontal rotary wing, offers powerful thrust levels, and a unique ability to change the direction of the thrust almost instantly. Rotor blades are designed to withstand tremendous transverse centrifugal loadings, and responding to a number of aerodynamic harmonic vibratory forcing frequencies. To reduce the weight and increase the strength, the blades are made of composite materials. The blades consist of the skin, spar, and trailing stiffener. In this study, static and dynamic behaviors of cyclocopter rotor blades are analyzed by using MSC/NASTRAN.

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Aerodynamic performance enhancement of cycloidal rotor according to blade pivot point movement and preset angle adjustment

  • Hwang, In-Seong;Kim, Seung-Jo
    • International Journal of Aeronautical and Space Sciences
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    • v.9 no.2
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    • pp.58-63
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    • 2008
  • This paper describes aerodynamic performance enhancement of cycloidal rotor according to the blade pivot point movement and the blade preset angle adjustment. Cycloidal blade system which consists of several blades rotating about an axis in parallel direction and changing its pitch angle periodically, is a propulsion mechanism of a new concept vertical take off and landing aircraft, cyclocopter. Based on the designed geometry of cyclocopter, numerical analysis was carried out by a general purpose commercial CFD program, STAR-CD. According to tills analysis, the efficiency of cycloidal rotor could be improved more than 15% by the introduced methods.

Optimized Structure Design of Composite Cyclocopter Rotor System using RSM (반응면 기법을 이용한 복합재료 사이클로콥터 로터의 최적 구조 설계)

  • Hwang In Seong;Hwang Chang Sup;Kim Min Ki;Kim Seung Jo
    • Composites Research
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    • v.18 no.4
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    • pp.52-58
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    • 2005
  • A cyclocopter propelled by the cycloidal blade system, which can be described as a horizontal rotary wing, is a new concept of VTOL vehicle. In this paper, optimized structure design is carried out for the aerodynamically optimized cyclocopter rotor system. Database is obtained fer design variables such as stacking sequence (ply angles), number of plies and spar locations through MSC/NASTRAN and optimum values are determined by RSM and some other optimizing processes. For the rotor system including optimized blade and composite hub m, the maximum stress by static analysis is within the failure criteria. And the rotor system is designed for the purpose of avoiding possible dynamic instabilities by inconsistency between frequencies of rotor rotation and some low natural frequencies of rotor.

Optimized design of composite Cyclocopter rotor system using RSM (반응면 기법을 이용한 복합재료 사이클로콥터 로터의 최적설계)

  • Hwang, Chang-Sup;Hwang, In-Seong;Kim, Min-Ki;Kim, Seung-Jo
    • Proceedings of the Korean Society For Composite Materials Conference
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    • pp.163-166
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    • 2005
  • 사이클로콥터는 회전축에 평행하게 회전하는 블레이드로 구성된 사이클로이드 블레이드 시스템으로부터 추력을 얻는 수직이착륙 무인기이다. 본 논문에서는 공기역할을 고려한 최적 설계를 통해 결정된 로터 형상을 갖는 사이클로콥터에 대해서 구조 해석을 수행하였다. 복합재료 블레이드의 적층각, 적층수 등을 MSC/NASTRAN 과 반응면 기법 등에 의해서 결정하였다. 블레이드를 포함한 로터 정적 해석을 통해 각 요소가 허용 응력 이내의 값을 가짐을 확인하였고, 동적 해석을 통해 주요 저차 모드가 로터 회전과 불일치하게 함으로써 공진의 가능성을 없앴다.

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