Gust Load Alleviation of an Aeroelastic System Using Nonlinear Control

Abstract

The author develops a nonlinear longitudinal model of an aircraft modeled by rigid fuselage, tail, and wing, where the wing is attached to the fuselage with a torsional spring. The main focus of this research is to retain the full nonlinearities associated with the system and to perform gust load alleviation for the model by

Aircraft Design with Active Load Alleviation and Natural Laminar Flow

“…1 Representative airfoil C p and geometries (adapted from Joslin [10]). Previous studies have addressed the key components of the GLA design problem: 1) find the worst-case gust for a given airplane [19][20][21][22][23][24]; 2) design the aircraft or wing structure to sustain a given gust encounter [25][26][27][28]; and 3) design a GLA controller for a given airplane [29][30][31]. Still others have examined the integrated problem of concurrently designing an aircraft with its GLA system [7][8][9].…”