L., “ Airplane Math Modeling for Active Control Design,” Proceedings of the 44th AGARD Structure and Materials Panel, AGARD, 1977, pp. 4.1–4.11. H., “ A Mixed Variational Formulation Based on Exact Intrinsic Equations or Dynamics of Moving Beams,” International Journal of Solids and Structures, Vol. 26, No. 11, 1990, pp. 1253–1273. S., “ Nonlinear Aeroelasticity of a Very Flexible Blended-Wing-Body Aircraft,” Journal of Aircraft, Vol. 47, No. 5, 2010, pp. 1539–1553. S., “ Nonlinear Flight Dynamics of Very Flexible Aircraft,” Journal of Aircraft, Vol. 44, No. 5, 2007, pp. 1528–1545. L., “ Modeling of High Aspect Ratio Active Flexible Wings for Roll Control,” 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA Paper 2002-1719, 2002. and Murua J., Consistent Structural Linearization in Flexible Aircraft Dynamics with Large Rigid-Body Motion, AIAA, Reston, VA, 2014, pp. 528–538. and Cardona A., Flexible Multibody Dynamics-A Finite Element Approach, Wiley, Chichester, England, U.K., 2001. E., Introduction to Aircraft Aeroelasticity and Loads, Wiley, Hoboken, NJ, 2008. and Wierzbanowski T., “ Technical Findings, Lessons Learned, and Recommendations Resulting from the Helios Prototype Vehicle Mishap,” NATO/RTO AVT-145 Workshop on Design Concepts, Processes and Criteria for UAV Structural Integrity, Florence, Italy, 2007.
Wings dst viewer full#
J., “ SUGAR Truss Braced Wing Full Scale Aeroelastic Analysis and Dynamically Scaled Wind Tunnel Model Development,” 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA Paper 2015-1171, 2015. Even on the aspect-ratio-10 case, which would traditionally be considered as a linear problem, it can be shown that the torque loads are considerably affected by nonlinearity. Torque behavior is problem specific and therefore difficult to generalize.
In contrast, the in-plane and axial loads are significantly underestimated using linear analyses. Load envelopes show that vertical shear and bending moments are predicted well by the linear analyses, even for the aspect-ratio-26 case, providing that the linearization is performed about the trimmed geometry. The gust analysis is also carried out using a linear approach (linearizing the equations of motion about an undeformed or trimmed geometry) to understand how nonlinearities influence the loads and dynamic behavior of aircraft as the aspect ratio increases. These aircraft are modeled in a nonlinear aeroelastic framework, featuring a geometrically exact beam formulation coupled with unsteady aerodynamics, and subjected to a gust loads process adapted for nonlinear systems. Three variants of a conceptual aircraft, featuring wing aspect ratios of 10, 18, and 26, are sized using an industrially inspired procedure to obtain realistic structures of existing and future designs. This paper considers the effect of geometric nonlinearity on gust load analyses of high-aspect-ratio commercial aircraft.
0 kommentar(er)
