Passive Gust Loads Alleviation in a Truss-Braced Wing Using Integrated Dampers

Christopher P Szczyglowski; Simon A Neild; Branislav Titurus; Jason Z Jiang; Jonathan E Cooper; Etienne Coetzee

Passive Gust Loads Alleviation in a Truss-Braced Wing Using Integrated Dampers

Christopher P Szczyglowski, Simon A Neild, Branislav Titurus, Jason Z Jiang, Jonathan E Cooper, Etienne Coetzee

Research output: Chapter in Book/Report/Conference proceeding › Conference Contribution (Conference Proceeding)

Abstract

Gust load cases tend to be critical for sizing the wing components and therefore methods of gust loads alleviation are necessary in order to reduce the overall weight of the wing structure. In this paper a method of gust loads alleviation for a truss-braced wing will be introduced which uses linear, rotational, viscous dampers co-located at the hinge joints connecting the truss structure to the wing to provide damping and thereby loads relief to the stress levels during a ”1-cosine” gust. The aeroelastic model is based on the NASA/Boeing SUGAR VOLT truss-braced wing and MSC.Nastran is used throughout the study to compute the gust response. It is found that large values of torsional viscous damping coefficient are required in order to provide moderate loads relief across the wing. Furthermore, it is found that a damper placed at the strut-fuselage joint is more beneficial than a damper located at the strut-wing joint due to its consistent performance across a range of gusts.

Original language	English
Title of host publication	Proceedings of the 17th International Forum on Aeroelasticity and Structural Dynamics, Como, Italy
Number of pages	13
Publication status	Published - 28 Jun 2017

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Projects

1 Finished

AWI - two FECs 193238 + 193801 - Airbus lead partner

Calderon, D. E., Eaton, A. J., Francis, D., Francois, G., Hawkes, L., Hewson, W. J. R., Howcroft, C., Reis, T. M. D., Stodieck, O. A., Szczyglowski, C. P. & Cooper, J. E.

1/07/14 → 30/09/18

Project: Research

Student Theses

Passive Aeroelastic Control In Truss-Braced Wings Using Vibration Suppression

Author: Szczyglowski, C. P., 23 Jan 2020

Supervisor: Neild, S. A. (Supervisor), Titurus, B. (Supervisor) & Jiang, J. Z. (Supervisor)

Student thesis: Doctoral Thesis › Doctor of Philosophy (PhD)

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Cite this

Szczyglowski, C. P., Neild, S. A., Titurus, B., Jiang, J. Z., Cooper, J. E., & Coetzee, E. (2017). Passive Gust Loads Alleviation in a Truss-Braced Wing Using Integrated Dampers. In Proceedings of the 17th International Forum on Aeroelasticity and Structural Dynamics, Como, Italy

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title = "Passive Gust Loads Alleviation in a Truss-Braced Wing Using Integrated Dampers",

abstract = "Gust load cases tend to be critical for sizing the wing components and therefore methods of gust loads alleviation are necessary in order to reduce the overall weight of the wing structure. In this paper a method of gust loads alleviation for a truss-braced wing will be introduced which uses linear, rotational, viscous dampers co-located at the hinge joints connecting the truss structure to the wing to provide damping and thereby loads relief to the stress levels during a ”1-cosine” gust. The aeroelastic model is based on the NASA/Boeing SUGAR VOLT truss-braced wing and MSC.Nastran is used throughout the study to compute the gust response. It is found that large values of torsional viscous damping coefficient are required in order to provide moderate loads relief across the wing. Furthermore, it is found that a damper placed at the strut-fuselage joint is more beneficial than a damper located at the strut-wing joint due to its consistent performance across a range of gusts.",

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Passive Gust Loads Alleviation in a Truss-Braced Wing Using Integrated Dampers. / Szczyglowski, Christopher P ; Neild, Simon A ; Titurus, Branislav ; Jiang, Jason Z ; Cooper, Jonathan E; Coetzee, Etienne.

Proceedings of the 17th International Forum on Aeroelasticity and Structural Dynamics, Como, Italy. 2017.

Research output: Chapter in Book/Report/Conference proceeding › Conference Contribution (Conference Proceeding)

TY - GEN

T1 - Passive Gust Loads Alleviation in a Truss-Braced Wing Using Integrated Dampers

AU - Szczyglowski, Christopher P

AU - Neild, Simon A

AU - Titurus, Branislav

AU - Jiang, Jason Z

AU - Cooper, Jonathan E

AU - Coetzee, Etienne

PY - 2017/6/28

Y1 - 2017/6/28

N2 - Gust load cases tend to be critical for sizing the wing components and therefore methods of gust loads alleviation are necessary in order to reduce the overall weight of the wing structure. In this paper a method of gust loads alleviation for a truss-braced wing will be introduced which uses linear, rotational, viscous dampers co-located at the hinge joints connecting the truss structure to the wing to provide damping and thereby loads relief to the stress levels during a ”1-cosine” gust. The aeroelastic model is based on the NASA/Boeing SUGAR VOLT truss-braced wing and MSC.Nastran is used throughout the study to compute the gust response. It is found that large values of torsional viscous damping coefficient are required in order to provide moderate loads relief across the wing. Furthermore, it is found that a damper placed at the strut-fuselage joint is more beneficial than a damper located at the strut-wing joint due to its consistent performance across a range of gusts.

AB - Gust load cases tend to be critical for sizing the wing components and therefore methods of gust loads alleviation are necessary in order to reduce the overall weight of the wing structure. In this paper a method of gust loads alleviation for a truss-braced wing will be introduced which uses linear, rotational, viscous dampers co-located at the hinge joints connecting the truss structure to the wing to provide damping and thereby loads relief to the stress levels during a ”1-cosine” gust. The aeroelastic model is based on the NASA/Boeing SUGAR VOLT truss-braced wing and MSC.Nastran is used throughout the study to compute the gust response. It is found that large values of torsional viscous damping coefficient are required in order to provide moderate loads relief across the wing. Furthermore, it is found that a damper placed at the strut-fuselage joint is more beneficial than a damper located at the strut-wing joint due to its consistent performance across a range of gusts.

M3 - Conference Contribution (Conference Proceeding)

BT - Proceedings of the 17th International Forum on Aeroelasticity and Structural Dynamics, Como, Italy

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