Development of a Cyclogyro-Based Flying Robot With Variable Attack Angle Mechanisms

Tanaka, Kazuo; Suzuki, Ryôhei; Emaru, Takanori; Higashi, Yoshiyuki; Wang, H.O.

doi:10.1109/tmech.2007.905720

Cited by 13 publications

(12 citation statements)

References 12 publications

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“…The present study employs the variable AOA system proposed by Tanaka et al (2007). A schematic diagram of the system is presented in Fig.…”

Section: Operating Principlementioning

confidence: 99%

“…These parameters were selected to take the same values as in the optimally designed model introduced by Tanaka et al (2007). h p was set to be 0°.…”

Section: Model Specificationsmentioning

confidence: 99%

“…In recent research, Tanaka et al (2007) developed a cyclogyro and varied its design parameters (wing length, wing number, etc.) to determine the combination that could generate the largest lift force.…”

Section: Introductionmentioning

confidence: 99%

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Flow measurement around a cycloidal propeller

Nakaie

Ohta

Hishida

2010

J Vis

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An experimental investigation was conducted to study the flow around a cycloidal propeller. Flow fields were obtained using a particle image velocimetry system whose data acquisition was synchronized with the propeller's angular position. The chord-based Reynolds number was Re c = u r c/t = 1.4 9 10 4 , where u r is the rotational velocity of the propeller and c is the chord length of the airfoil. Flow characteristics such as mean velocity, vorticity and the RMS value of velocity fluctuation were derived from the measurements. The results demonstrated the presence of a downwash around the propeller during the generation of lift. Detailed observations around each airfoil visualized distinct vortex shedding and reattaching flow at certain phase angles of the propeller.

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“…The present study employs the variable AOA system proposed by Tanaka et al (2007). A schematic diagram of the system is presented in Fig.…”

Section: Operating Principlementioning

confidence: 99%

“…These parameters were selected to take the same values as in the optimally designed model introduced by Tanaka et al (2007). h p was set to be 0°.…”

Section: Model Specificationsmentioning

confidence: 99%

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Flow measurement around a cycloidal propeller

Nakaie

Ohta

Hishida

2010

J Vis

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“…Our future subject is to apply the control scheme of this paper to real extremely complex aircrafts developed by the authors [20], [21], [22]. …”

Section: Discussionmentioning

confidence: 99%

A practical design approach to automatic model construction and controller design for F16 aircraft

Ogura

Chen

Tanaka

2013

2013 International Conference on Fuzzy Theory and Its Applications (iFUZZY)

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This paper presents a practical design approach to automatic model construction and controller design for the F16 aircraft. The automatic model construction and controller design are realized using the framework of a Takagi-Sugeno (T-S) fuzzy modeling and control. Any trimmed equilibriums in addition to the complicated dynamics describing in an F16 aircraft simulator are considered and automatically converted to T-S fuzzy models around any trimmed equilibriums. A linear matrix inequality based design is carried out to automatically obtain stable nonlinear T-S fuzzy controllers according to the considered trimmed equilibriums. Control performance of the designed controllers are tested for the original dynamics (not T-S fuzzy models). The testing results demonstrate the utility of the practical design approach to automatic model construction and controller design.

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“…[26][27][28][29] With the aim of analyzing the existence of a steering center for whatever may be the dimension of the mechanical pitch control system Figure 4 may be considered. In other words, it was searched for the blade pitch angle so that there is the steering center and then it was compared to the real pitch angle imposed by the mechanical system given by equation (4). Therefore, let us consider that the blade is at an azimuthal position É oscillating around the pivot point A.…”

Section: Mechanism and Blade Position Controlmentioning

confidence: 99%

Analytical modeling of a cyclorotor in hovering state

Leger

Páscoa

Xisto

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In the paper it is proposed and described in detail a mathematical model that is able to assist in the design of cycloidal rotors. The method is formulated on a semi-empirical way including unsteady aerodynamic effects that are based on first principles. It is able to predict the overall generated thrust and the power required by the operation of the cycloidal rotor. The model also includes a kinematic package that can provide an instantaneous design and animation of the cycloidal rotor under different regimes of operation. For validation it was addressed three different rotor configurations where it was varied several rotor parameters, namely: pitch amplitude; pitching axis location; blade chord; airfoil thickness; phase angle of eccentricity. It was shown that the proposed model is able to provide a good estimation of thrust and power when compared with the experimental data from these different sources, showing that the semi-empirical approach could be applied in a more general way.

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Development of a Cyclogyro-Based Flying Robot With Variable Attack Angle Mechanisms

Cited by 13 publications

References 12 publications

Flow measurement around a cycloidal propeller

Flow measurement around a cycloidal propeller

A practical design approach to automatic model construction and controller design for F16 aircraft

Analytical modeling of a cyclorotor in hovering state

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