Computational aeroelasticity framework for analyzing flapping wing micro air vehicles

AIAA Journal

Volumn 47, Issue 8, 2009, Pages 1865-1878

  Chimakurthi, Satish Kumar ^a,c   Tang, Jian ^a,c   Palacios, Rafael ^b,c   Carlos, E S Cesnik ^b,c   Shyy, Wei ^a,c  

^a UNIVERSITY OF MICHIGAN   (United States)

^b IMPERIAL COLLEGE LONDON   (United Kingdom)

^c Department of Aerospace Engineering ^*

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMIC LOADING; ARBITRARY GEOMETRY; COMPUTATIONAL AERO ELASTICITY; COMPUTATIONAL FRAMEWORK; FINITE-ELEMENT; FLAPPING WING MICRO AIR VEHICLE; FLEXIBLE WINGS; FLIGHT REGIME; FLOW SOLVER; FLUID DENSITIES; FLUID PHYSICS; GEOMETRICALLY NONLINEAR STRUCTURES; MICRO AERIAL VEHICLE; NAVIER-STOKES SOLVER; PRESSURE-BASED; RECTANGULAR WINGS; REDUCED FREQUENCY; SLENDER WINGS; SMALL SIZE; STRUCTURAL MODELS; THRUST COEFFICIENTS; TIP DISPLACEMENT;

AEROSPACE VEHICLES; ASPECT RATIO; ELASTICITY; EQUATIONS OF MOTION; FLIGHT DYNAMICS; GAS DYNAMICS; MICRO AIR VEHICLE (MAV); MODEL STRUCTURES; NONLINEAR EQUATIONS; REYNOLDS NUMBER; SPACECRAFT; STRUCTURAL DYNAMICS; THREE DIMENSIONAL;

WINGS;

EID: 69949146010     PISSN: 00011452     EISSN: None     Source Type: Journal    
DOI: 10.2514/1.38845     Document Type: Article

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