• Title/Summary/Keyword: 날개짓 비행체

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Aerodynamic Characteristics of a Three-Dimensional Wing in Heave Oscillation (히브진동하는 3차원 날개 공력특성)

  • Chin, Chul-Soo;Kim, Tae-Wan;Lee, Hyoung-Wook;Han, Cheol-Heui
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.39 no.10
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    • pp.905-911
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    • 2011
  • With the progress of micro actuator technology, studies on the development of micro air flapping wing vehicles are actively undergoing. In the present study, the changes of both lift and thrust characteristics of the wings are investigated using a boundary element method. Lift of the heaving wing is not generated when the wing is beating with smaller frequencies than 1 Hz. Thrust increases with amplitude and frequency. As the wing's taper and aspect ratios increase, both lift and thrust also increase. Results on the pitching oscillation and flapping motion will be included in the future work.

Development of a Radio Controlled Ornithopter 'Songgolmae' (무선조종 날개짓 비행체 '송골매' 개발)

  • Chang, Jo-Won
    • Proceedings of the KSME Conference
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    • 2004.04a
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    • pp.1993-1998
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    • 2004
  • The present study was carried out to develop highly efficient RC ornithopter 'Songgolmae' powered by motor and battery. Designed electric ornithopter weighs 277 grams and has 3 channels radio control. 1t runs on an electric motor by a lithium polymer battery and has a gear ratio of about $75{\sim}95$ to 1 to flap its 88 cm wingspan. The aerodynamic performance of the ornithopter, applied to a flapping motion only, was validated by flight tests. Flight times have exceeded 23 minutes until the battery was used up. The flight test results indicate that the ornithopter developed here has sufficient thrust to propel itself in a forward flight. From the economical point of view and the handling of the RC ornithopter, it can be said that the developed robot ornithopter is an effective RC ornithopter. This radio controlled ornithopter flies its way high into the sky just like a real bird flies.

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Ornithopter actuator characteristics analysis by motion capture experiment (모션캡쳐 실험을 통한 조류모방 날갯짓 비행체 구동 특성 분석)

  • Gim, Hakseong;Kim, Seungkeun;Suk, Jinyoung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.3
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    • pp.173-179
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    • 2017
  • This paper analyzes actuator characteristics for main wing and tail surfaces of an ornithopter by using a motion capture test. Experiments with the ornithopter are conducted indoor, and its fuselage is held on a jig to reduce interaction with vibration generated by flapping motion. The motion capture system detects the movement of markers attached on the main wing and tail wing tip. Experimental results show that the main wings tend to change its amplitude according to the flapping frequency, and the lift and thrust generation simulation is implemented by applying the experimental results and the ornithopter specification to Modified Strip Theory. Step input excitation is applied for experimental analysis of the tail wing in horizontal and vertical directions. As a result, horizontal and vertical tail wings have different characteristics in terms of overshoot, final value, damping ratio and natural frequency because they have different wing structures and linkages.

Development of a Robot Ornithopter 'Songgolmae' (로봇 날개짓 비행체 '송골매' 개발)

  • Chang, J.W.
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.11 no.1
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    • pp.5-16
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    • 2003
  • The present study was carried out to develop highly efficient RC ornithopter 'Songgolmae' powered by motor and battery. Designed electric ornithopter, which has the dimension of O.88m(W)${\times}$0.56m(L)${\times}$0.15m(H), is smaller than a conventional ornithopter. This ornithopter weighs 277 grams and has 3 channels radio control. It runs on an electric motor by a lithium polymer battery and has a gear ratio of about 75${\sim}$95 to 1 to flap its 88 cm wingspan. The aerodynamic performance of the ornithopter, applied to a flapping motion only, was validated by flight tests. Flight times have exceeded 23 minutes until the battery was used up. The flight test results indicate that the ornithopter developed here has sufficient thrust to propel itself in a forward flight. From the economical point of view and the handling of the RC ornithopter, it can be said that the developed robot ornithopter is an effective RC ornithopter. This robot ornithopter flies its way high into the sky just like a real bird flies. The robot ornithopter is used for a wide range of missions.

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Development of a Micro Ornithopter with a Weight of 20 gram (중량 20그램의 초소형 날갯짓 비행체 개발)

  • Lee, Jae-Moon;Chang, Jo-Won;Jung, Yun-Sik
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.10
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    • pp.82-92
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    • 2005
  • The present study was carried out in order to develop a remote-controlled micro ornithopter with a weight of 20 gram. This ornithopter has three channel radio control. It runs on two direct-current type pager motors powered by a lithium polymer battery which flaps its 35cm wings. The performance of an ornithopter, applied to a flapping motion only, was validated by flight tests. The flight test results indicate that the ornithopter developed here has sufficient thrust to propel itself.

Development of Wing and Driving Mechanism for Flapping Micro Air Vehicle using Piezoelectirc and Electroactive Materials. (압전 특성을 이용한 날개짓 비행체의 날개 구동 장치 개발)

  • 이광락;박지형;김성주
    • Proceedings of the Korean Society of Precision Engineering Conference
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    • 2003.06a
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    • pp.709-712
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    • 2003
  • The existing technical limitation makes engineer imitate nature to solve engineering problems. Recently Micro Air Vehicle(MAV) imitating the mechanism of birds or insects is being developed. Especially Ultra Flite supported by DARPA is studying hummingbird aerodynamics to relate that information to MAV. To drive MAV bender piezoelectric(PZT) actuators are used due to the convinience of control and the small size. But the displacement of the PZT actuators are very small, and the wing driving mechanism which amplifies the stroke generated by the PZT actuators has constraints in design and manufacture because of the small dimension. In this paper a wing design concept and a efficient driving mechanism are proposed. Electroactive polymers(EAPs) are used as wing mechanism actuators. Using OpenGL the mechanisms are simulated graphically. Also a prototype actuator is being developed and verified by digital Mockup with CATIA. Basic kinematics of the mechanism is studied.

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Improvement of Flapping Air Vehicle by Using Axiomatic Design (공리적 설계를 이용한 Flapping 비행체의 성능 개선)

  • 성호석;차성운;이경수
    • Proceedings of the Korean Society of Precision Engineering Conference
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    • 1997.10a
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    • pp.684-688
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    • 1997
  • The human species has been able to fly for about a century - with the help of aircraft of various kinds. Recently. air vehicles which are like an insect or a bird with flapping wings have been appeared, although many of them are experimental flight vehicle. However, the rubber-powered flapping vehicle is put to practical use such as toy, which flies for some seconds. In this paper, we analyze and evaluate above the rubber-powered flight vehicle using axiomatic design and will present new four flapping wing model.

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Lift Force Variation of Flapping Wing (날개짓 비행체의 양력 변위)

  • Hong, Young-Sun
    • Journal of the Korea Institute of Military Science and Technology
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    • v.10 no.1
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    • pp.33-43
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    • 2007
  • Using the more common conventional chordwise aerodynamic approach, flapping a flat plate wing with zero degree chordwise pitch angle of attack and no relative wind should not produce lift. However, in hover, with no forward relative velocity and zero degree chordwise pitch angle of attack, flapping flat plate wings does in fact produce lift. In the experiments peformed for this paper, the flapping motion is considered pure(downstroke and upstroke) with no flapping stroke plane inclination angle. No changes in chordwise pitch angle are made. The total force is measured using a force transducer and the net aerodynamic force is determined from this measured total force by subtracting the experimentally determined inertial contribution. These experiments were repeated at various flapping frequencies and for various wing planform sizes for flat plate wings. The trends in the aerodynamic lift variation found using a force transducer have nearly identical shape for various flapping frequencies and wing planform sizes.