Nonlinear Aeroelastic Analysis of Complete Aircraft in Subsonic Flow

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Flight Dynamics of Highly Flexible Flying Wings (2006, unknown): “2 Structural Model The geometrically-exact, intrinsic equations for the dynamics of a general, non-uniform, twisted, curved, anisotropic beam, undergoing large deformation, are given as F ′ + (k̃ + κ̃)F + f = Ṗ + Ω̃P (1) M ′ + (k̃ + κ̃)M + (ẽ1 + γ̃)F + m = Ḣ + Ω̃H + Ṽ P (2) V ′ + (k̃ + κ̃)V + (ẽ1 + ”
Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics (2012, background): “The primary structures (wing, fuselage, empennage) are modelled as composite curvilinear beams capable of large deflections and global rotations, but under the assumption of small local strains [9, 174].”
Nonlinear Flight Dynamics of Very Flexible Aircraft (2005, unknown): “[14] developed a formulation for the complete modeling of a HALE-type vehicle.”
Flight Dynamics of Highly Flexible Aircraft (2008, background): “They extended the work to nonlinear aeroelastic stability analysis [6] and the design of an output feedback controller to suppress flutter and alleviate gust loads [7].”