Design Optimization of Aircraft Engine-Mount Systems.

Design Optimization of Aircraft Engine-Mount Systems.

Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeled as a rigid body connected to a flexible base representing the nacelle. The base (nacelle) is modeled with mass and stiffness matrices and structural damping using finite element modeling....

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Main Author: Ashrafiuon, Hashem.
Format: Villanova Faculty Authorship
Language:English
Published: 1993
Online Access:http://ezproxy.villanova.edu/login?url=https://digital.library.villanova.edu/Item/vudl:173876
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spelling Design Optimization of Aircraft Engine-Mount Systems.
Ashrafiuon, Hashem.
Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeled as a rigid body connected to a flexible base representing the nacelle. The base (nacelle) is modeled with mass and stiffness matrices and structural damping using finite element modeling. The mounts are modeled as three-dimensional springs with hysteresis damping. The objective is to select the stiffness coefficients and orientation angles of the individual mounts in order to minimize the transmitted forces from the engine to the nacelle. Meanwhile, the mounts have to be stiff enough not to allow the engine deflection to exceed its limits under static and low frequency loadings. It is shown that with an optimal system the transmitted forces may be reduced significantly particularly when orientation angles are also treated as design variables. The optimization problems are solved using a constraint variable metric approach. The closed form derivatives of the engine vibrational amplitudes with respect to design variables are derived in order to determine the objective function gradients and consequently a more effective optimization search technique.
1993
Villanova Faculty Authorship
vudl:173876
Journal of Vibration and Acoustics 115, 1993, 463-467.
en
dc.title_txt_mv Design Optimization of Aircraft Engine-Mount Systems.
dc.creator_txt_mv Ashrafiuon, Hashem.
dc.description_txt_mv Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeled as a rigid body connected to a flexible base representing the nacelle. The base (nacelle) is modeled with mass and stiffness matrices and structural damping using finite element modeling. The mounts are modeled as three-dimensional springs with hysteresis damping. The objective is to select the stiffness coefficients and orientation angles of the individual mounts in order to minimize the transmitted forces from the engine to the nacelle. Meanwhile, the mounts have to be stiff enough not to allow the engine deflection to exceed its limits under static and low frequency loadings. It is shown that with an optimal system the transmitted forces may be reduced significantly particularly when orientation angles are also treated as design variables. The optimization problems are solved using a constraint variable metric approach. The closed form derivatives of the engine vibrational amplitudes with respect to design variables are derived in order to determine the objective function gradients and consequently a more effective optimization search technique.
dc.date_txt_mv 1993
dc.format_txt_mv Villanova Faculty Authorship
dc.identifier_txt_mv vudl:173876
dc.source_txt_mv Journal of Vibration and Acoustics 115, 1993, 463-467.
dc.language_txt_mv en
author Ashrafiuon, Hashem.
spellingShingle Ashrafiuon, Hashem.
Design Optimization of Aircraft Engine-Mount Systems.
author_facet Ashrafiuon, Hashem.
dc_source_str_mv Journal of Vibration and Acoustics 115, 1993, 463-467.
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author_sort Ashrafiuon, Hashem.
dc_date_str 1993
dc_title_str Design Optimization of Aircraft Engine-Mount Systems.
description Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeled as a rigid body connected to a flexible base representing the nacelle. The base (nacelle) is modeled with mass and stiffness matrices and structural damping using finite element modeling. The mounts are modeled as three-dimensional springs with hysteresis damping. The objective is to select the stiffness coefficients and orientation angles of the individual mounts in order to minimize the transmitted forces from the engine to the nacelle. Meanwhile, the mounts have to be stiff enough not to allow the engine deflection to exceed its limits under static and low frequency loadings. It is shown that with an optimal system the transmitted forces may be reduced significantly particularly when orientation angles are also treated as design variables. The optimization problems are solved using a constraint variable metric approach. The closed form derivatives of the engine vibrational amplitudes with respect to design variables are derived in order to determine the objective function gradients and consequently a more effective optimization search technique.
title Design Optimization of Aircraft Engine-Mount Systems.
title_full Design Optimization of Aircraft Engine-Mount Systems.
title_fullStr Design Optimization of Aircraft Engine-Mount Systems.
title_full_unstemmed Design Optimization of Aircraft Engine-Mount Systems.
title_short Design Optimization of Aircraft Engine-Mount Systems.
title_sort design optimization of aircraft engine-mount systems.
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language English
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