Structure-control interaction and the design of piezoceramic actuated adaptive airfoils

Steadman, D.; Griffin, Steven; Hanagud, S.

doi:10.2514/6.1994-1747

Cited by 11 publications

(8 citation statements)

References 4 publications

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“…Many researchers focused on the application of piezoelectrics to the blades of rotary wing aircraft to improve their performance and effectiveness. Steadman et al [4] showed an application of a piezoceramic actuator for camber control in helicopter blades. Giurgiutiu et al [5] has researched performance improvement on rotor blades using strain-induced actuation methods (using PZTs).…”

Section: Introductionmentioning

confidence: 99%

Theoretical and Experimental Analysis of Hysteresis in Piezocomposite Airfoils Using Preisach Model

Bilgen

Friswell

Inman

2011

Journal of Aircraft

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In this paper, the classical (scalar) Preisach model is used to predict hysteresis observed in several Macro-Fiber Composite actuated piezocomposite bimorph devices: 1) two cantilevered beams, 2) a simply supported thin airfoil, and 3) a cascading bimorph thick airfoil. This paper contributes to the research field by examining the effectiveness of the scalar Preisach model for operational and wind-tunnel tested piezocomposite airfoils in the presence of aerodynamic and inertial loading and subjected to two different electrical boundary conditions. A low-speed opencircuit wind tunnel is used for experimental analysis. The flow speed is used as a parameter to understand the effect of nonuniform aerodynamic loading on the accuracy of the model. In addition, the excitation frequency is used as a parameter to understand the effect of inertial (mass) loading. It was observed that the aerodynamic loading, up to 19 m=s, has a negligible effect on the aerodynamic output of the airfoils considered in this research. The classical Preisach model is capable of predicting the hysteresis observed in all of the samples tested with an average prediction error less than 6.8% for a 0.5 Hz input signal and less than 9.3% for a 1 Hz input signal. The increasing-decreasing and decreasing-increasing first-order transition curves are both found to be equally successful in developing the Preisach model for all samples.

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Section: Introductionmentioning

confidence: 99%

Theoretical and Experimental Analysis of Hysteresis in Piezocomposite Airfoils Using Preisach Model

Bilgen

Friswell

Inman

2011

Journal of Aircraft

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“…In the 1990s, several types of smart materials and structures were investigated, including piezoelectric materials, electrostrictive materials, magnetostrictive materials, shape memory alloys, and fiber optic sensors (McGowan et al, 1999; Martin et al, 1998). Several studies have focused on morphing rotor structures using piezoelectric materials (Barrett, 1996; Barrett et al, 1998; Barrett and Stutts, 1997; Ehlers and Weisshaar, 1990; Giurgiutiu et al, 1994; Rodgers et al, 1997; Steadman et al, 1994), shape memory alloys (Roglin et al, 1994; Roglin and Hanagud, 1996), and magnetostrictive materials (Giurgiutiu et al, 1995). Piezoelectric actuators were used in morphing airfoil wings (Pinkerton and Moses, 1997) and in the control fins of a missile (Barrett and Stutts, 1998).…”

Section: Introductionmentioning

confidence: 99%

Morphing aircraft based on smart materials and structures: A state-of-the-art review

Sun

Guan

Liu

et al. 2016

Journal of Intelligent Material Systems and Structures

274

137

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A traditional aircraft is optimized for only one or two flight conditions, not for the entire flight envelope. In contrast, the wings of a bird can be reshaped to provide optimal performance at all flight conditions. Any change in an aircraft’s configuration, in particular the wings, affects the aerodynamic performance, and optimal configurations can be obtained for each flight condition. Morphing technologies offer aerodynamic benefits for an aircraft over a wide range of flight conditions. The advantages of a morphing aircraft are based on an assumption that the additional weight of the morphing components is acceptable. Traditional mechanical and hydraulic systems are not considered good choices for morphing aircraft. “Smart” materials and structures have the advantages of high energy density, ease of control, variable stiffness, and the ability to tolerate large amounts of strain. These characteristics offer researchers and designers new possibilities for designing morphing aircraft. In this article, recent developments in the application of smart materials and structures to morphing aircraft are reviewed. Specifically, four categories of applications are discussed: actuators, sensors, controllers, and structures.

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“…Many researchers focused on the application of piezoelectric materials to the blades of rotary-wing aircraft to improve their performance and effectiveness. Steadman et al (1994) showed an application of a piezoceramic actuator for camber control in helicopter blades. Giurgiutiu et al (1994) have researched the performance improvement on rotor blades using strain-induced actuation methods (using PZTs).…”

Section: Introductionmentioning

confidence: 99%

A novel unmanned aircraft with solid-state control surfaces: Analysis and flight demonstration

Bilgen

Butt

Day

et al. 2012

Journal of Intelligent Material Systems and Structures

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This article presents a completely servo-less, piezoelectric controlled, wind tunnel and flight tested, remotely piloted aircraft that has been developed by the 2010 Virginia Tech Wing Morphing Design Team (a senior design project between the Departments of Mechanical Engineering and Aerospace and Ocean Engineering). A type of piezocomposite actuator, the Macro-Fiber Composite, is used for changing the camber of all control surfaces on the aircraft. The aircraft is analyzed theoretically for its aerodynamic characteristics to aid the design of the piezoelectric control surfaces. A vortex lattice analysis complemented the database of aerodynamic derivatives used to analyze control response. Steady-state roll rates were measured in a wind tunnel and were compared to a similar aircraft with servomotor actuated control surfaces. The theoretical analysis and wind tunnel testing demonstrated the stability and control authority of the concept, culminating in the first flight of the completely Macro-Fiber Composite controlled aircraft on 29 April 2010. An electric motor-driven propulsion system is used to generate thrust, and all systems are powered with a single lithium polymer battery. This vehicle became the first completely Macro-Fiber Composite controlled, flight tested aircraft. It is also known to be the first fully solid-state piezoelectric material controlled, nontethered, flight tested fixed-wing aircraft.

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Structure-control interaction and the design of piezoceramic actuated adaptive airfoils

Cited by 11 publications

References 4 publications

Theoretical and Experimental Analysis of Hysteresis in Piezocomposite Airfoils Using Preisach Model

Theoretical and Experimental Analysis of Hysteresis in Piezocomposite Airfoils Using Preisach Model

Morphing aircraft based on smart materials and structures: A state-of-the-art review

A novel unmanned aircraft with solid-state control surfaces: Analysis and flight demonstration

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