TY - GEN
T1 - Development of a finite element model of warping inflatable wings
AU - Rowe, Johnathan M.
AU - Smith, Suzanne Weaver
AU - Simpson, Andrew
AU - Jacob, Jamey
AU - Scarborough, Stephen
PY - 2006
Y1 - 2006
N2 - This paper presents development of a structural model of warping inflatable wings. In order to quickly and effectively analyze the effects of aerodynamic loading and to consider design options for warping actuation, a detailed finite element model is required. The methodology used to develop and initially validate a finite element model of an inflatable wing is described in this paper. The wing is a complex structural system including intricate geometry, internal pressurization and a woven fabric shell structure. This effort includes determination of material properties via laboratory tests. These are verified with finite element simulations of simple inflatable cylinders constructed of similar material. The process used to create a finite element simulation of the wing is presented, including modeling assumptions and nonlinear analysis stages. Results for various loadings of interest are included. Finally, the paper presents initial validation of the finite element model using results of static cantilever wing bending and twisting loads applied at the inflatable wing tip. Although the model represents important deformation characteristics of the inflatable wing, it is generally too stiff compared to experimental results. Future modifications to the model and further validation are also discussed.
AB - This paper presents development of a structural model of warping inflatable wings. In order to quickly and effectively analyze the effects of aerodynamic loading and to consider design options for warping actuation, a detailed finite element model is required. The methodology used to develop and initially validate a finite element model of an inflatable wing is described in this paper. The wing is a complex structural system including intricate geometry, internal pressurization and a woven fabric shell structure. This effort includes determination of material properties via laboratory tests. These are verified with finite element simulations of simple inflatable cylinders constructed of similar material. The process used to create a finite element simulation of the wing is presented, including modeling assumptions and nonlinear analysis stages. Results for various loadings of interest are included. Finally, the paper presents initial validation of the finite element model using results of static cantilever wing bending and twisting loads applied at the inflatable wing tip. Although the model represents important deformation characteristics of the inflatable wing, it is generally too stiff compared to experimental results. Future modifications to the model and further validation are also discussed.
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U2 - 10.2514/6.2006-1697
DO - 10.2514/6.2006-1697
M3 - Conference contribution
AN - SCOPUS:34247104966
SN - 1563478080
SN - 9781563478086
T3 - Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
SP - 1277
EP - 1294
BT - Collection of Technical Papers - 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
T2 - 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Y2 - 1 May 2006 through 4 May 2006
ER -