Our objective is to develop a nonlinear aerodynamic and nonlinear structural interaction (NANSI) methodology as an expedient aeroelastic tool to handle continuous dynamic motion of morphing vehicles/wings throughout the flight regimes of subsonic to transonic speeds. The proposed morph vehicles for method demonstration is the Lockheed Folding wing (the Folding wing). Preliminary results on Flut...

A new design concept in the development of vertical takeoff and landing aircraft with high forward flight speed capability is that of the X-Wing. The X-Wing is a stiff, bearingless helicopter rotor system which can be stopped in flight and the blades used as two forward-swept wings and two aft-swept wings. Because of the unusual configuration in the fixed-wing mode, there is a high potential fo...

A high-fidelity numerical formulation is presented for the high-speed aeroelastic behavior of slender composite wings. The compressible flow is modeled using the 3-D Euler equations on a deformable mesh, and an asymptotic approximation of the 3-D kinematically-nonlinear equations of elasticity models the anisotropic slender structure. The transfer of the distributed loads and displacements at t...

The development of a non-certainty-equivalent adaptive control system for the control of a nonlinear aeroelastic system is the subject of this paper. The prototypical aeroelastic wing section considered here includes structural nonlinearity and a single control surface for the purpose of control. Its dynamical model has two-degree-of-freedom and describes the plunge and pitch motion. It is assu...

This paper presents investigation effects of a sharp edged gust on aeroelastic behavior and time-domain response of a typical section model using Jones approximate aerodynamics for pure plunging motion. Flutter analysis has been done by using p and p-k methods developed for presented finite-state aerodynamic model for a typical section model (airfoil). Introduction of gust analysis as a linear ...

Recent significant improvements to the development of CFD-based unsteady aerodynamic reduced-order models (ROMs) are implemented into the FUN3D unstructured flow solver. These improvements include the simultaneous excitation of the structural modes of the CFD-based unsteady aerodynamic system via a single CFD solution, minimization of the error between the full CFD and the ROM unsteady aerodyna...

The article investigates the numeric simulation of two-way aeroelastic processes applied to the experimental phase of a compressor; physical, mathematical, rigid and grid models of the system “gas – rotor – stator” have been worked out; 2 FSI (two-way Fluid-Structure Interaction) calculations have been performed on the evaluation of the interaction between a gas-dynamic flow and a deformable ro...

Abstract. This article describes the methodology adopted to implement an ILAF control system on a three surface aeroelastic demonstrator with the aim of shaping fuselage modal dynamics. General concepts used, hypotheses formulated and numerical results are provided to show that a numerical simulation involving reduced order models for aeroelastic models is suitable, even at a very early design ...

Aeroelasticity is a critical consideration in the design of gas turbine engines, both for stability and forced response. Current aeroelastic models cannot provide highdelity aerodynamics in a form suitable for design or control applications. In this thesis low-order, highdelity aerodynamic models are developed using systematic model order reduction from computational uid dynamic (CFD) methods. ...

This paper considers the aeroelastic optimization of a subsonic transport wingbox under a variety of static and dynamic aeroelastic constraints. Three types of design variables are utilized: structural variables (skin thickness, stiffener details), the quasi-steady deflection scheduling of a series of control surfaces distributed along the trailing edge for maneuver load alleviation and trim at...