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 ...

As a collaborative effort among government aerospace research laboratories, an advanced version of a widely used computational fluid dynamics code, OVERFLOW2.1z, was recently released. This latest version includes additions to model multiple flexible, rotating blades. This paper describes how the OVERFLOW code is applied to improve the accuracy of airload computations from the linear lifting li...

In this paper, the aeroelastic flutter stability of an impeller is investigated numerically with single passage and full annulus URANS simulations carried out on one side a stage configuration including strut other multistage in which two additional diffusers are considered downstream. The robustness relying use multiple frequency phase-lagged boundary conditions put to test especially case for...

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...

This paper presents an adaptive control approach for flutter suppression of a performance adaptive aeroelastic wing equipped with a variable camber continuous trailing edge flap design. The adaptive control approach is based on the optimal control modification method augmented to a linear quadratic gaussian optimal control design. A model reduction based on a singular perturbation approach is p...

This work is focused on the implementation of a general multibody analysis framework for the real-time simulation of complex systems. It is applied to the modeling of the Semi-Articulated Soft-InPlane (SASIP) rotor recently installed and tested on the Wing and Rotor Aeroelastic Testing System (WRATS) at NASA Langley. The aim is to obtain a detailed, yet efficient virtual experiment, based on st...

Despite the benefits of composite structures, it is only recently that the main load bearing structures in large aircraft such as the Boeing 787 and Airbus A350 have started to be manufactured using carbon fibre composites. Even then, the unique directionality properties of composite laminates and design possibilities have yet to be exploited to improve the aircraft performance. In this study a...

Imagine yourself looking out the window on a commercial flight at the aircraft engine outside. For four years, I worked at Honeywell Aerospace as product design engineer in a research team investigating flutter and forced response issues in turbomachinery for aircraft engines. Flutter is an aeroelastic issue that can cause near-instantaneous and catastrophic part failure. It results from the un...

ABSTRACT: An approximate approach for the frequencyand time-domain aeroelastic analysis of bridge decks is presented. The aerodynamic transfer functions are approximated as a linear function with the coefficients determined through minimization of the weighted error between the exact and approximated transfer function. The weighting function in optimization is introduced for the improved approx...

This paper considers the control of coupled aeroelastic aircraft model with Variable Camber Continuous Trailing Edge Flap (VCCTEF) system. The relative motion between two adjacent flaps is constrained and this actuation constraint problem is converted into an output covariance constraint problem, and therefore can be formulated using linear matrix inequalities (LMIs). A set of LMI conditions is...