Aircraft Control via Variable Cant-Angle Winglets

Bourdin, P.; Gatto, A.; Friswell, Michael I.

doi:10.2514/1.27720

Cited by 89 publications

(68 citation statements)

References 11 publications

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“…In [2] and [15], a canted winglet concept whose actuation mechanism is similar to ours was demonstrated; however, its function was different in that it was used for roll control rather than yaw control.…”

Section: Literature Reviewmentioning

confidence: 84%

Novel Dihedral-Based Control of Flapping-Wing Aircraft With Application to Perching

2013

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Abstract-We describe the design of an aerial robot inspired by birds and the underlying theoretical developments leading to novel control and closed-loop guidance algorithms for a perching maneuver. A unique feature of this robot is that it uses wing articulation to control the flight path angle as well as the heading angle. It lacks a vertical tail for improved agility, which results in unstable lateraldirectional dynamics. New closed-loop motion planning algorithms with guaranteed stability are obtained by rewriting the flight dynamic equations in the spatial domain rather than as functions of time, after which dynamic inversion is employed. It is shown that nonlinear dynamic inversion naturally leads to proportionalintegral-derivative controllers, thereby providing an exact method for tuning the gains. The capabilities of the proposed bioinspired robot design and its novel closed-loop perching controller have been successfully demonstrated with perched landings on a human hand.

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Section: Literature Reviewmentioning

confidence: 84%

Novel Dihedral-Based Control of Flapping-Wing Aircraft With Application to Perching

2013

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“…The idea of using an asymmetric dihedral for yaw control can be traced to a recent paper by Bourdin et al [6]. Tran and Lind [7] examined the stability of a flexible wing aircraft for various wing deflection configurations.…”

Section: A Literature Reviewmentioning

confidence: 99%

Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings

et al. 2012

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The purpose of this paper is to analyze and discuss the performance and stability of a tailless micro aerial vehicle with flexible articulated wings. The dihedral angles can be varied symmetrically on both wings to control the aircraft speed independently of the angle of attack and flight-path angle, while an asymmetric dihedral setting can be used to control yaw in the absence of a vertical tail. A nonlinear aeroelastic model is derived, and it is used to study the steadystate performance and flight stability of the micro aerial vehicle. The concept of the effective dihedral is introduced, which allows for a unified treatment of rigid and flexible wing aircraft. It also identifies the amount of elasticity that is necessary to obtain tangible performance benefits over a rigid wing. The feasibility of using axial tension to stiffen the wing is discussed, and, at least in the context of a linear model, it is shown that adding axial tension is effective but undesirable. The turning performance of an micro aerial vehicle with flexible wings is compared to an otherwise identical micro aerial vehicle with rigid wings. The wing dihedral alone can be varied asymmetrically to perform rapid turns and regulate sideslip. The maximum attainable turn rate for a given elevator setting, however, does not increase unless antisymmetric wing twisting is employed.

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“…The reader is referred to an excellent compendium of papers [54] which showcases some of the work done in this area until circa 2000. The idea of using cant-angle winglets for control was investigated experimentally by Bourdin, Gatto and Friswell [8,28] for larger aircraft operating at high Reynolds numbers. However, their analysis was restricted to calculating the aerodynamic moments arising from the use of cant-angle winglets.…”

Section: Literature Reviewmentioning

confidence: 99%

Bio-Inspired Integrated Sensing and Control Flapping Flight for Micro Aerial Vehicles

Chung¹

2012

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Aircraft Control via Variable Cant-Angle Winglets

Cited by 89 publications

References 11 publications

Novel Dihedral-Based Control of Flapping-Wing Aircraft With Application to Perching

Novel Dihedral-Based Control of Flapping-Wing Aircraft With Application to Perching

Dynamics and Performance of Tailless Micro Aerial Vehicle with Flexible Articulated Wings

Bio-Inspired Integrated Sensing and Control Flapping Flight for Micro Aerial Vehicles

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