#### DMCA

## Active Authority Enhancement of Piezoelectric Actuator Design via Mechanical Resonance and Electrical Tailoring

### Citations

361 |
The art of electronics,
- Paul, Winfield
- 1995
(Show Context)
Citation Context ... C nsare the effective capacitance and negative capacitance, respectively.sHere, the negative capacitance can be achieved using an operational amplifier to form a negative impedance converter circuit =-=[18]-=-. LR AC VC Cp S : PZT actuator Cn: Negative capacitor Trailing edge flap Shunt circuit Figure 3: Schematic of PZT actuator with shunt circuit and negative capacitor. In order to integrate the PZT actu... |

127 |
Formulas for Natural Frequencies and Mode
- Blevins
- 1984
(Show Context)
Citation Context ...a bender actuator, the first eigenfunction is given by, ( ) sin( ) sinh( ) {cos( ) cosh( )}l l l lx x x x xβ β β βφ α= − − − , (3) where α andsβ denote the coefficients of clamped beam eigenfunctions =-=[19]-=-, l indicates the length of the beam, and x is the distance along span of the beam. For stack and tube actuators, ( ) sin( ) 2 x x l piφ = . (4) For each actuator, the equations of motions can be writ... |

114 |
Damping of Structural Vibrations with Piezoelectric Materials and Passive electrical
- Hagood, Flotow
- 1991
(Show Context)
Citation Context ...cal tailoring In general, the frequency response (Eq. (19)) of the resonant actuation system with the shunt circuit will intersect that of the system without the shunt circuit at two invariant points =-=[10,15]-=-.sThe location of the intersection points depend on the inductance tuning δ defined in Eq. (21).sWhen the magnitudes of these two points are equal, the inductance tuning, δ*, for the series RL configu... |

23 |
Status of Application of Smart Structures Technology to Rotorcraft Systems,”
- Chopra
- 2000
(Show Context)
Citation Context ...op actuation mechanisms exploiting the characteristics of piezoelectric ceramic materials.sAmong them, one of the very promising concepts for helicopter rotor control is the active trailing edge flap =-=[1,2,3]-=-.sSuch an actuation system can be used with multi-functional roles to suppress vibration and noise, increase aeromechanical stability, and decrease blade loads. While current piezoelectric materials-b... |

20 |
Active-Passive Hybrid Piezoelectric Networks for Vibration Control:
- Tang, Wang
- 2001
(Show Context)
Citation Context ...abilities [13,14]. The integration of the passive and active approach, often referred to as an active-passive hybrid piezoelectric network, has shown to achieve promising results in vibration control =-=[15]-=-.sThe electric network tailoring idea proposed in this paper is built upon these previous investigations, but with completely different design philosophy and criterion. l ll (b) stack(a) bender (c) tu... |

11 |
On the structural damping characteristics of active piezoelectric actuators with passive shunt,”
- Tsai, Wang
- 1999
(Show Context)
Citation Context ...tor active authority around the tuned circuit frequency [10-12].sSeveral researchers have proposed the “negative capacitance” concept to enhance the networks’ multiple mode and broadband capabilities =-=[13,14]-=-. The integration of the passive and active approach, often referred to as an active-passive hybrid piezoelectric network, has shown to achieve promising results in vibration control [15].sThe electri... |

8 |
Control of a Ring Structure With Multiple Active-Passive Hybrid Piezoelectric
- Tsai, Wang
- 1996
(Show Context)
Citation Context ..., aerodynamic and inertial contributions FA can be expressed in terms of the trailing edge flap deflection angle δ : A A A AF M C Kδ δ δ= + + s(11) in which, 2 21 2A air f IH M C U c L hδ ρ ∞= +s=-=(12)-=- 2 21 2A air fH C C U c Lδ ρ ∞= s(13) 2 21 2A H air f CF K C U c L hδ ρ ∞= +s(14) where c and Lf are the chord length and span of trailing edge flap, respectively.sSubscript ‘A’ indicates the trailin... |

7 |
Bench-Top Characterization of An Active Rotor Blade Flap System Incorporating C-Block
- Clement, Brei, et al.
- 1998
(Show Context)
Citation Context ...gal propeller moments due to the rotation of blade (see Figure 2).sAssuming that the trailing edge flap deflection angles are small, the inertial and propeller moments can be expressed as: Ih Iδδ= s=-=(6)-=- 2 2ssin( )sCF f xg f xgh M d x M d xδ δ= Ω ≈ Ωs(7) where δ is a trailing flap deflection angle, and Ω is the rotation speed of blade. Iδ, Mf, d and xcg are the flap mass moment of inertia, the mass o... |

7 |
An X-frame Actuator Servo-Flap Actuation System for Rotor Control
- Prechtl, Hall
(Show Context)
Citation Context ...ncompressible aerodynamic model based on Theodorsen’s theory. The hinge moment coefficients in terms of flap deflection angle δ is given by 12 10 4 10 5 1 1( ) ( ) 2 2H C T T C k T T Tδ pi pi = − + −s=-=(8)-=- 12 11 4 11 1 1( ) 4 4H C T T bC k T T b U Uδ pi pi ∞ ∞ = − + s(9) 2 32 1 2H C T b Uδ pi ∞ = s(10) where coefficients T are geometric parameters defined by Theodorsen, U∞ and b are the relative win... |

7 |
Development of a Modal Model for Simultaneous Active and Passive Piezoelectric Vibration Suppression
- Agnes
- 1995
(Show Context)
Citation Context ...ound in Ref. [17].sOnce all the coefficients are found, aerodynamic and inertial contributions FA can be expressed in terms of the trailing edge flap deflection angle δ : A A A AF M C Kδ δ δ= + + s=-=(11)-=- in which, 2 21 2A air f IH M C U c L hδ ρ ∞= +s(12) 2 21 2A air fH C C U c Lδ ρ ∞= s(13) 2 21 2A H air f CF K C U c L hδ ρ ∞= +s(14) where c and Lf are the chord length and span of trailing edge f... |

6 |
Analysis and Testing of Mach Scaled Helicopter Rotor in Hover with Piezoelectric Bender Actuated Trailing Edge Flaps,” SPIE’s Smart Structures and Materials
- Koratkar, Chopra
- 1998
(Show Context)
Citation Context ...denote the coefficients of clamped beam eigenfunctions [19], l indicates the length of the beam, and x is the distance along span of the beam. For stack and tube actuators, ( ) sin( ) 2 x x l piφ = . =-=(4)-=- For each actuator, the equations of motions can be written as follows: 1 2 1 P P P a M q C q K q k Q F V k k q + + + = = + s(5) where Mp, Cp and Kp are the mass, damping, and open-circuit stiffne... |

6 |
Induced-shear piezoelectric actuators for rotor blade trailing edge flaps,
- Centolanza, Smith, et al.
- 2002
(Show Context)
Citation Context ...ed.sThe trailing edge flap deflections are computed to quantify the active authority.sFor the purpose of comparison, a baseline actuation system is first defined based on the design presented in Ref. =-=[9]-=-: the length of the baseline PZT tube actuator is 4 inches, outer radius R osis assumed to be 0.175 inches, the tube wall thickness is 0.1 inches, the flap length is 20% of rotor length, 7.2 inches, a... |

3 |
Hover Testing of a Small Scale Rotor with On-Blade Elevons,”
- Fulton, Ormiston
- 2001
(Show Context)
Citation Context ... the beam. For stack and tube actuators, ( ) sin( ) 2 x x l piφ = . (4) For each actuator, the equations of motions can be written as follows: 1 2 1 P P P a M q C q K q k Q F V k k q + + + = = + s=-=(5)-=- where Mp, Cp and Kp are the mass, damping, and open-circuit stiffness terms of the actuator, and Q is the charge on the piezoelectric material.sk1 represents the coupling between the mechanical and e... |

2 |
Design of Piezostack Driven Trailing Edge Flap Actuator for Helicopter Rotors,” Smart Materials and Structures,
- Lee, Chopra
- 2001
(Show Context)
Citation Context ...(see Figure 2).sAssuming that the trailing edge flap deflection angles are small, the inertial and propeller moments can be expressed as: Ih Iδδ= s(6) 2 2ssin( )sCF f xg f xgh M d x M d xδ δ= Ω ≈ Ωs=-=(7)-=- where δ is a trailing flap deflection angle, and Ω is the rotation speed of blade. Iδ, Mf, d and xcg are the flap mass moment of inertia, the mass of flap, the distance of flap center of mass from el... |

2 |
New Method for Multiple-mode Shunt Damping of Structural Vibration Using a Single Piezoelectric Transducer
- Behrens, Moheimani, et al.
(Show Context)
Citation Context ...tor active authority around the tuned circuit frequency [10-12].sSeveral researchers have proposed the “negative capacitance” concept to enhance the networks’ multiple mode and broadband capabilities =-=[13,14]-=-. The integration of the passive and active approach, often referred to as an active-passive hybrid piezoelectric network, has shown to achieve promising results in vibration control [15].sThe electri... |

2 |
General Theory of Aerodynamic Instability and the Mechanism of Flutter,”
- Theodorson
- 1935
(Show Context)
Citation Context ...o i n l R R R Rpiβ − + 3 Aerodynamic and inertial loads at trailing edge flap hinge The aerodynamic model for trailing edge flap used in this study is based on the incompressible theory by Theodorsen =-=[17]-=-. The total hinge moment is comprised of the aerodynamic, inertial and centrifugal propeller moments due to the rotation of blade (see Figure 2).sAssuming that the trailing edge flap deflection angles... |

1 |
A Parametric Study for Actively Controlled Trailing Edge Flaps
- Milgram, Chopra
- 1998
(Show Context)
Citation Context ...op actuation mechanisms exploiting the characteristics of piezoelectric ceramic materials.sAmong them, one of the very promising concepts for helicopter rotor control is the active trailing edge flap =-=[1,2,3]-=-.sSuch an actuation system can be used with multi-functional roles to suppress vibration and noise, increase aeromechanical stability, and decrease blade loads. While current piezoelectric materials-b... |

1 |
Active Load Control of an Articulated Composite Rotor Blade via Dual Trailing Edge Flaps
- Kim, Smith, et al.
- 2003
(Show Context)
Citation Context ...op actuation mechanisms exploiting the characteristics of piezoelectric ceramic materials.sAmong them, one of the very promising concepts for helicopter rotor control is the active trailing edge flap =-=[1,2,3]-=-.sSuch an actuation system can be used with multi-functional roles to suppress vibration and noise, increase aeromechanical stability, and decrease blade loads. While current piezoelectric materials-b... |