Nonlinear Dynamic Inversion of a Flexible Aircraft

Nonlinear Dynamic Inversion Control of a Miniature Morphing Aircraft

Stability Result for Dynamic Inversion Devised to Control Large Flexible Aircraft

Abstract High performance aircraft of the future will be designed lighter, more maneuverable, and operate over an ever expanding flight envelope. One of the largest differences from the flight control perspective between current and future advanced aircraft is elasticity. Over the last decade, dynamic inversion methodology has gained considerable popularity in application to highly maneuverable...

Nonlinear Aeroelasticity of a Very Flexible Blended-Wing-Body Aircraft

This paper presents a study on the coupled aeroelastic/flight dynamic stability and gust response of a blendedwing-body aircraft that derives from the U.S. Air Force’s High Lift-Over-Drag Active (HiLDA) wing experimental model. An effective method is used to model very flexible blended-wing-body vehicles based on a low-order aeroelastic formulation that is capable of capturing the important str...

A Nonlinear Modal Aeroservoelastic Analysis Framework for Flexible Aircraft

We present a nonlinear formulation in modal coordinates of the equations of motion of a flexible aircraft. It relies on the projection of the intrinsic equations of geometrically-nonlinear composite beams on the linear normal modes at a reference condition, which are coupled with 2D unsteady aerodynamics. The resulting description is suitable for nonlinear dynamic analysis and control design, w...

Nonlinear Aeroelastic Modeling and Analysis of Fully Flexible Aircraft

This paper introduces an approach to effectively model the nonlinear aeroelastic behavior of fully flexible aircraft. The study is conducted based on a nonlinear strainedbased finite element framework in which the developed low-order formulation captures the nonlinear (large) deflection behavior of the wings, and the unsteady subsonic aerodynamic forces acting on them. Instead of merely conside...