Prediction of Preliminary Maximum Wing Bending Moments Under Discrete Gust

Fournier, Edouard; Grihon, Stéphane; Bès, Christian; Klein, Thierry

doi:10.2514/1.c035329

Cited by 3 publications

(3 citation statements)

References 23 publications

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“…Even though different gust prediction methods were developed in recent years to Different methodologies have been proposed in recent years to quickly identify worst-case gust load scenarios [50,51]. However, as the focus of the present work is on gust loads at design cruise inflow conditions, the number of required simulations to predict the critical gust scenario is manageable.…”

Section: A Prestudy -Critical Gust Loadsmentioning

confidence: 99%

Approach for Aerodynamic Gust Load Alleviation by Means of Spanwise-Segmented Flaps

Ullah¹,

Lutz²,

Klug³

et al. 2023

Journal of Aircraft

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Active gust load alleviation techniques exhibit a high potential in significantly reducing the transient gust loads on aircraft. In this work the aerodynamic potential of trailing-edge flaps and leading-edge flaps is numerically studied with the purpose to significantly reduce the structural gust loads. The utilized spanwise-segmented flaps represent slight modifications of existing devices for high-lift and maneuvering. The investigations based on unsteady Reynolds-averaged Navier–Stokes computations are conducted by employing a generic wing–fuselage aircraft configuration at transonic flow conditions. Idealized discrete “[Formula: see text]”-type vertical gusts that are relevant for the certification process are used as representative atmospheric disturbances. The focus of this paper is to introduce a practicable prediction method for required trailing- and leading-edge flap deflections for a significant mitigation of gust-induced wing loads. The three-dimensional flap deflections are determined by parametric two-dimensional simulations at representative wing sections. Different extensions of the estimation approach are investigated to assess the influence of the wing planform, the finite wing span, the aerodynamic phase lags, and the flap scheduling. It is shown that the trailing- and leading-edge flaps are promising in terms of alleviation of gust-induced wing bending and wing torsional moments, respectively. However, at high leading-edge flap deflections that are necessary for a full compensation of the wing torsional moment large-scale flow separation is identified. The introduced gust load alleviation approach indicates a good transferability between two-dimensional airfoil and three-dimensional wing aerodynamics for unsteady flap deflections.

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Section: A Prestudy -Critical Gust Loadsmentioning

confidence: 99%

Approach for Aerodynamic Gust Load Alleviation by Means of Spanwise-Segmented Flaps

Ullah¹,

Lutz²,

Klug³

et al. 2023

Journal of Aircraft

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“…Cook et al (2017) investigated the effects of aircraft flexibility on 1 g and gust loads based on an intrinsic beam theory to understand the effects of large geometrically nonlinear deformations on the loads due to level fight and atmospheric turbulence in the form of 1-cosine gusts. Fournier et al (2019) presented a reliable and fast methodology for estimating critical load cases for weight-variant aircrafts at the preliminary design phase. After identifying the set of preliminary parameters, the proposed methodology used the orthogonal greedy algorithm (OGA) to identify the coefficient of the second-order polynomial response surfaces from an initial database aircraft, which included the weight-variant aircraft.…”

Section: Introductionmentioning

confidence: 99%

Gust response analysis based on a nonlinear structural model and the unsteady aerodynamics of a flexible aircraft

Masrour

Sadati²,

Shahravi³

2023

AEAT

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Purpose This study aims to simulate gust effects on the aeroelastic behavior of a flexible aircraft. The dynamic response of the system for different discreet gust excitations is obtained using numerical simulations. Design/methodology/approach Coupled dynamics, including rigid and flexible body coordinates, are considered for modeling the dynamic behavior of the aircraft. Wing is considered flexible and other parts are considered rigid. Wing is modeled with nonlinear Euler Bernoulli beam. Moreover, unsteady aerodynamics based on the Wagner function are used for aerodynamic loading, and the results are compared with those of quasi-steady aerodynamics. Findings Von Kármán continuous gust is applied to this aircraft. In addition, the discrete “1- cosine” gust with different gust lengths is applied to the aircraft, and the maximum and minimum accelerations are computed. It is shown that the nonlinear modeling of the system represents the actual behavior and causes limit cycle oscillation phenomena. Originality/value This methodology can yield a relatively simple dynamic model for high aspect ratio aircrafts to provide insights into the vehicles’ dynamics, which can be available early in the design cycle.

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“…The number of simulations to build a meta-model is still high, but negligible compared to the case without such a method. Other applications of meta-models are found in Fournier et al (2019) applying a second-order polynomial expansion or in Nazzeri et al (2015) using a meta-model relying on artificial neural networks.…”

Section: Introductionmentioning

confidence: 99%

Assessment of discrete wind gust parameters: Towards the worst-case scenario of a FSI application in form of an inflated hemisphere

Nayer

Breuer

2022

Journal of Wind Engineering and Industrial Aerodynamics

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Prediction of Preliminary Maximum Wing Bending Moments Under Discrete Gust

Cited by 3 publications

References 23 publications

Approach for Aerodynamic Gust Load Alleviation by Means of Spanwise-Segmented Flaps

Approach for Aerodynamic Gust Load Alleviation by Means of Spanwise-Segmented Flaps

Gust response analysis based on a nonlinear structural model and the unsteady aerodynamics of a flexible aircraft

Assessment of discrete wind gust parameters: Towards the worst-case scenario of a FSI application in form of an inflated hemisphere

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