In this work, energy harvesting from limit cycle oscillation of low aspect ratio rectangular cantilever plates in low subsonic flow by ionic polymer metal composite is considered. The plate is modeled in according to classic plate theory with Von-Karman strain-displacement relations for modeling large deflections due to midplane stretching. Aerodynamics flow is modeled based on modified vortex lattice aerodynamics model. Linear and nonlinear aeroelastic characteristics of the considered model are accurately examined and the effects of ionic polymer metal composite energy harvesting properties on flutter margin and limit cycle oscillation amplitudes are investigated. The obtained results show that output power of 1:75 mW is generated when the flow velocity reaches to 60 m=s, and position of ionic polymer metal composite on the plate has great effect on the amount of power produced. The extraction of energy from plate vibration in conjunction with large strain characteristics of ionic polymer metal composite materials produces static deflection of plate. This static deflection produces stiffness hardening of the entire system, accordingly reduces the amplitude of limit cycle oscillation. Obtained results show that ionic polymer metal composite actuator has more influence on limit cycle oscillation of plate, while its effect on flutter instability is negligible.
This work presents energy harvesting from the limit cycle oscillation of low aspect ratio rectangular cantilever wings in supersonic ow. The wing is modeled according to the classical plate theory with von-Karman strain-displacement relations for modeling large de ections due to mid-plane stretching. The aerodynamic pressure is evaluated based on the quasi-steady rst-order piston theory. Linear and nonlinear aeroelastic characteristics of the considered model are accurately examined and the e ects of Ionic Polymer Metal Composite (IPMC) energy harvesting on utter margin and limit cycle oscillation amplitudes are investigated. It is shown that the position of IPMC on the wing has a great e ect on the amount of harvested power. Since IPMC induces a high level of strain, it produces the static de ection of the wing. This static de ection produces sti ness hardening of the entire system, and, accordingly, can greatly reduce the amplitude of limit cycle oscillation. Obtained results show that the IPMC actuator has more in uence on the limit cycle oscillation of the wing, while its e ect on utter instability is negligible.
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