A Novel Unmanned Aircraft with Solid-State Control Surfaces: Analysis and Flight Demonstration

Bilgen, Onur; Butt, Lauren M.; Day, Steven R.; Sossi, Craig; Weaver, Joseph; Wolek, Artur; Mason, William H.; Inman, Daniel J.

doi:10.2514/6.2011-2071

Cited by 25 publications

(11 citation statements)

References 23 publications

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“…Wood (2007) achieved lift off of a tethered fly-like model using only piezoelectric actuation. Bilgen et al (2007Bilgen et al ( , 2009 presented the first application of solid-state piezocomposite actuators on a 0.76-m wingspan morphing wing air vehicle and conducted further research and flight tests on morphing fixed-wing airfoils (Bilgen et al, 2010a(Bilgen et al, , 2010b(Bilgen et al, , 2012Bilgen and Friswell, 2014;Butt et al, 2010aButt et al, , 2010b. In 2013, Bounthisane et al (2015) developed a carbon-fiber wing modeled after the Great Blue Heron actuated with MFCs.…”

Section: Literature Reviewmentioning

confidence: 99%

Parametric modal analysis of an induced-strain actuated wing-like plate for pitch and heave coupling response

Hauris

Bilgen

2020

Journal of Intelligent Material Systems and Structures

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This article investigates the feasibility of a plate-like flapping wing with varying geometric and boundary conditions actuated by surface-bonded piezoelectric material devices. The most influential structural parameters that vary dynamic response and heave–pitch mode coupling are investigated. An analytically and experimentally validated dynamic finite element model is developed to analyze the structure. A parametric analysis is conducted by varying critical geometric parameters and boundary conditions, such as aspect ratio, actuator position, actuator angle, clamp size, and position; substrate thickness variation; and substrate-to-actuator-thickness ratio. Response metrics representing heave and pitch motions are taken as longitudinal curvature and lateral slope, respectively—the surface regression analysis and results leading to these choices are presented. Maximum longitudinal curvature and lateral slope amplitudes and phase shifts are reported for key parameter choices. Longitudinal curvature to lateral slope coupling is achieved with the introduction of a leading edge stiffener to the otherwise uniform thickness plate. Conditions and parameters that lead to and influence heave–pitch coupling are presented and discussed in detail. This article presents a unique approach to flapping mode of flight compared to the literature. The article proposes a purely induced-strain actuation approach rather than the typical “mechanisms” based approach.

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Section: Literature Reviewmentioning

confidence: 99%

Parametric modal analysis of an induced-strain actuated wing-like plate for pitch and heave coupling response

Hauris

Bilgen

2020

Journal of Intelligent Material Systems and Structures

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“…The NASA Langley Research Center developed piezoelectric macro fiber composites (MFCs) which have large bending flexibility and large ultimate tensile strain (4000 με) (Smart Material Corp, 2019). Many variable-camber wings based on MFCs had been researched in various attempts to improve their aerodynamic performance (Bilgen et al, 2010b, 2010c, 2011; Kochersberger et al, 2017; Molinari et al, 2015; Gamble and Inman, 2018). However, few previous researcher has applied axial pressure to improve the deformation or output power of these devices.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of axial-compressed macro-fiber composite bimorph with multi-layer parallel actuators for large deformation actuation

Wen

2020

Journal of Intelligent Material Systems and Structures

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Piezoelectric bimorphs have a promising application in morphing micro air vehicles; however, increasing the actuation displacement is a difficult point. Axial compression can be used to increase the deformation of the piezoelectric bimorph. Compared with piezoelectric ceramics, macro fiber composites offer higher flexibility. In this article, a large displacement actuator of axial-compressed macro fiber composite bimorph is proposed. A multi-layer parallel scheme of macro fiber composite bimorphs is presented to increase the output torque of piezoelectric bimorph within a limited space. The actuation performance of the axial-compressed macro fiber composite bimorph and its multi-layer parallel scheme are verified through quasi-static experiment and displacement tracking control test. The experimental results show that the end-free rotations of both the axial-compressed macro fiber composite bimorph and its multi-layer scheme achieve ±8.1°, which is 60% higher than that of a piezoelectric ceramics bimorph with the same length. The blocking torque of the single-layer macro fiber composite bimorph is 0.028 Nm. The proposed parallel bimorphs method can magnify output torques. In addition, the axial-compressed macro fiber composite bimorph can accurately track any displacement signals in the range of its actuation. It is a continuous and controllable piezoelectric bimorph with large displacement.

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“…Design, analysis, and validation of MFC-actuated morphing wings have been studied (Paradies and Ciresa, 2009;Prazenica et al, 2014;Wickramasinghe et al, 2011). Wind tunnel test and flight control test on the morphing wing MAVs are also presented (Bilgen et al, 2007a(Bilgen et al, , 2007b(Bilgen et al, , 2013Ohanian et al, 2013). The theoretical and experimental results demonstrated that the continuous surface of MFC-actuated morphing wings produced improved aerodynamic properties, wide actuation bandwidth, and adequate flight authority.…”

Section: Introductionmentioning

confidence: 99%

Dynamic shape control of piezocomposite-actuated morphing wings with vibration suppression

Wang

Zhou

Xun

et al. 2017

Journal of Intelligent Material Systems and Structures

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Aerodynamic properties and aeroelastic responses of morphing wings can be improved via active shape control using piezoelectric actuators. In this article, a type of piezocomposite material called macro-fiber composite is used for actuation to achieve shape control of the morphing wing. This study focuses on the vibration suppression of the wing during dynamic morphing motion in open-loop architecture. The aeroelastic model is established using finite element method and Theodorsen unsteady aerodynamic loads. Because the arbitrary selection of any admissible control voltage profiles will cause vibrations of the wing structure and fluctuations in aerodynamic lift, a dynamic shape control approach is presented to optimize the voltage profiles for the actuators. A proof-of-concept simulation is presented for a scaled high-aspect-ratio wing. The results show that continuous, smooth morphing motion with gentle aeroelastic responses can be realized by applying the optimum voltage profiles. The dynamic shape control performance of the morphing wing can be improved compared with step and ramp voltage profiles.

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A Novel Unmanned Aircraft with Solid-State Control Surfaces: Analysis and Flight Demonstration

Cited by 25 publications

References 23 publications

Parametric modal analysis of an induced-strain actuated wing-like plate for pitch and heave coupling response

Parametric modal analysis of an induced-strain actuated wing-like plate for pitch and heave coupling response

Experimental study of axial-compressed macro-fiber composite bimorph with multi-layer parallel actuators for large deformation actuation

Dynamic shape control of piezocomposite-actuated morphing wings with vibration suppression

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