Passive Gust Loads Alleviation in a Truss-Braced Wing Using an Inerter-Based Device

Christopher Patrick Szczyglowski; Simon A Neild; Branislav Titurus; Jason Zheng Jiang; Etienne Coetzee

doi:10.2514/1.C035452

Passive Gust Loads Alleviation in a Truss-Braced Wing Using an Inerter-Based Device

Christopher Patrick Szczyglowski, Simon A Neild, Branislav Titurus, Jason Zheng Jiang, Etienne Coetzee

Research output: Contribution to journal › Article (Academic Journal) › peer-review

10 Citations (Scopus)

399 Downloads (Pure)

Abstract

This paper presents a novel method for gust loads alleviation in a truss-braced wing in which an inerter-based device located in the truss-structure is used to reduce peak-loads during a discrete “1-cosine” gust. Three candidate layouts are considered, and the device parameters are optimized to target the response of the first three structural modes. It is demonstrated that either a single damper or a combination of inerter-based devices can be used to achieve a reduction of approximately 4% for spanwise locations inboard of the strut attachment point and that this reduction is consistent across the full range of gust gradients. Furthermore, it is noted that the inerter-based device has a significantly smaller damping coefficient than the case where just a damper is used and that the device parameter values are viable within the scope of an aerospace application.

Original language	English
Number of pages	12
Journal	Journal of Aircraft
Early online date	26 Aug 2019
DOIs	https://doi.org/10.2514/1.C035452
Publication status	Published - 2019

Research Groups and Themes

AWI

Keywords

gust loads alleviation
vibration suppresssion
inerter
nastran

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10.2514/1.C035452Licence: Unspecified

Full-text PDF (accepted author manuscript)
This is the author accepted manuscript (AAM). The final published version (version of record) is available online via American Institute of Aeronautics and Astronautics at https://arc.aiaa.org/doi/10.2514/1.C035452. Please refer to any applicable terms of use of the publisher.
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10 Citations
1 Conference Contribution (Conference Proceeding)

Passive Gust Load Alleviation in a Truss-Braced Wing Using an Inerter-Based Device
Szczyglowski, C. P., Neild, S., Titurus, B. & Jiang, J. Z., 10 Jan 2018, AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum. American Institute of Aeronautics and Astronautics Inc. (AIAA), 16 p. AIAA 2018-1958. (Journal of Aircraft).
Research output: Chapter in Book/Report/Conference proceeding › Conference Contribution (Conference Proceeding)

Open Access
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2 Citations (Scopus)

362 Downloads (Pure)

2 Finished

AWI - two FECs 193238 + 193801 - Airbus lead partner
Calderon, D. E. (Researcher), Eaton, A. J. (Student), Francis, D. (Student), Francois, G. (Researcher), Hawkes, L. (Student), Hewson, W. J. R. (Student), Howcroft, C. (Researcher), Reis, T. M. D. (Student), Stodieck, O. A. (Researcher), Szczyglowski, C. P. (Student) & Cooper, J. E. (Principal Investigator)
1/07/14 → 30/09/18
Project: Research
AWI: Agile Wing Integration - Nonlinear devices on a strut for loads control
Titurus, B. (Co-Investigator)
1/04/14 → 30/09/18
Project: Research

Passive Aeroelastic Control In Truss-Braced Wings Using Vibration Suppression
Szczyglowski, C. P. (Author), Neild, S. A. (Supervisor), Titurus, B. (Supervisor) & Jiang, J. Z. (Supervisor), 23 Jan 2020
Student thesis: Doctoral Thesis › Doctor of Philosophy (PhD)

File

Cite this

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title = "Passive Gust Loads Alleviation in a Truss-Braced Wing Using an Inerter-Based Device",

abstract = "This paper presents a novel method for gust loads alleviation in a truss-braced wing in which an inerter-based device located in the truss-structure is used to reduce peak-loads during a discrete “1-cosine” gust. Three candidate layouts are considered, and the device parameters are optimized to target the response of the first three structural modes. It is demonstrated that either a single damper or a combination of inerter-based devices can be used to achieve a reduction of approximately 4% for spanwise locations inboard of the strut attachment point and that this reduction is consistent across the full range of gust gradients. Furthermore, it is noted that the inerter-based device has a significantly smaller damping coefficient than the case where just a damper is used and that the device parameter values are viable within the scope of an aerospace application.",

keywords = "gust loads alleviation, vibration suppresssion, inerter, nastran",

author = "Szczyglowski, {Christopher Patrick} and Neild, {Simon A} and Branislav Titurus and Jiang, {Jason Zheng} and Etienne Coetzee",

year = "2019",

doi = "10.2514/1.C035452",

language = "English",

journal = "Journal of Aircraft",

issn = "0021-8669",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

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AU - Szczyglowski, Christopher Patrick

AU - Neild, Simon A

AU - Titurus, Branislav

AU - Jiang, Jason Zheng

AU - Coetzee, Etienne

PY - 2019

Y1 - 2019

N2 - This paper presents a novel method for gust loads alleviation in a truss-braced wing in which an inerter-based device located in the truss-structure is used to reduce peak-loads during a discrete “1-cosine” gust. Three candidate layouts are considered, and the device parameters are optimized to target the response of the first three structural modes. It is demonstrated that either a single damper or a combination of inerter-based devices can be used to achieve a reduction of approximately 4% for spanwise locations inboard of the strut attachment point and that this reduction is consistent across the full range of gust gradients. Furthermore, it is noted that the inerter-based device has a significantly smaller damping coefficient than the case where just a damper is used and that the device parameter values are viable within the scope of an aerospace application.

AB - This paper presents a novel method for gust loads alleviation in a truss-braced wing in which an inerter-based device located in the truss-structure is used to reduce peak-loads during a discrete “1-cosine” gust. Three candidate layouts are considered, and the device parameters are optimized to target the response of the first three structural modes. It is demonstrated that either a single damper or a combination of inerter-based devices can be used to achieve a reduction of approximately 4% for spanwise locations inboard of the strut attachment point and that this reduction is consistent across the full range of gust gradients. Furthermore, it is noted that the inerter-based device has a significantly smaller damping coefficient than the case where just a damper is used and that the device parameter values are viable within the scope of an aerospace application.

KW - gust loads alleviation

KW - vibration suppresssion

KW - inerter

KW - nastran

U2 - 10.2514/1.C035452

DO - 10.2514/1.C035452

M3 - Article (Academic Journal)

SN - 0021-8669

JO - Journal of Aircraft

JF - Journal of Aircraft

ER -

Passive Gust Loads Alleviation in a Truss-Braced Wing Using an Inerter-Based Device

Abstract

Research Groups and Themes

Keywords

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Research output

Passive Gust Load Alleviation in a Truss-Braced Wing Using an Inerter-Based Device

Projects

AWI - two FECs 193238 + 193801 - Airbus lead partner

AWI: Agile Wing Integration - Nonlinear devices on a strut for loads control

Student theses

Passive Aeroelastic Control In Truss-Braced Wings Using Vibration Suppression

Cite this