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Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring / Mohammadreza Amoozgar; Alexander Shaw; Jiaying Zhang; Michael Friswell

AIAA Journal, Volume: 57, Issue: 10, Pages: 4218 - 4225

Swansea University Authors: Mohammadreza, Amoozgar, Alexander, Shaw, Jiaying, Zhang, Michael, Friswell

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DOI (Published version): 10.2514/1.j057591

Abstract

In this paper, a new concept for morphing composite blades is proposed, and how this concept changes the twist distribution of the blade is explained. A change in the blade twist is obtained by adding a mass to the blade that produces an extra centrifugal force. This centrifugal force then may produ...

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Published in: AIAA Journal
ISSN: 0001-1452 1533-385X
Published: American Institute of Aeronautics and Astronautics (AIAA) 2019
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URI: https://cronfa.swan.ac.uk/Record/cronfa53415
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first_indexed 2020-02-03T19:23:29Z
last_indexed 2020-09-17T03:16:39Z
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spelling 2020-02-03T15:30:06.2290383 v2 53415 2020-02-03 Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring 56910e9937b39a1a96d6252845c385d3 Mohammadreza Amoozgar Mohammadreza Amoozgar true false 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 12b61893c794b14f11cf0a84cb947d0e 0000-0001-7308-5090 Jiaying Zhang Jiaying Zhang true false 5894777b8f9c6e64bde3568d68078d40 Michael Friswell Michael Friswell true false 2020-02-03 In this paper, a new concept for morphing composite blades is proposed, and how this concept changes the twist distribution of the blade is explained. A change in the blade twist is obtained by adding a mass to the blade that produces an extra centrifugal force. This centrifugal force then may produce a moment that can change the blade twist via the extension–twist or bend–twist coupling of the composite lamination. These types of couplings are present in antisymmetrically and symmetrically laminated beams, respectively. The dynamics of the rotating composite blade is modeled by using the geometrically exact fully intrinsic beam equations. The concentrated mass is considered as a nonstructural concentrated mass that has offsets with respect to the beam reference line. The nonlinear partial differential equations are discretized by using a time–space scheme, the converged results are compared with those reported in the literature, and very good agreement is observed. It is found that, for an antisymmetric lamination, the spanwise location of the concentrated mass affects the twist, whereas in the symmetric case, the chordwise position of the concentrated mass is the source of twist change. It is also found that introducing the concentrated mass to a real blade can change the twist dramatically. Journal Article AIAA Journal 57 10 4218 4225 American Institute of Aeronautics and Astronautics (AIAA) 0001-1452 1533-385X 1 10 2019 2019-10-01 10.2514/1.j057591 COLLEGE NANME COLLEGE CODE Swansea University 2020-02-03T15:30:06.2290383 2020-02-03T15:30:06.2290383 Mohammadreza Amoozgar 1 Alexander Shaw 0000-0002-7521-827X 2 Jiaying Zhang 0000-0001-7308-5090 3 Michael Friswell 4
title Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
spellingShingle Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
Mohammadreza, Amoozgar
Alexander, Shaw
Jiaying, Zhang
Michael, Friswell
title_short Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
title_full Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
title_fullStr Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
title_full_unstemmed Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
title_sort Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring
author_id_str_mv 56910e9937b39a1a96d6252845c385d3
10cb5f545bc146fba9a542a1d85f2dea
12b61893c794b14f11cf0a84cb947d0e
5894777b8f9c6e64bde3568d68078d40
author_id_fullname_str_mv 56910e9937b39a1a96d6252845c385d3_***_Mohammadreza, Amoozgar
10cb5f545bc146fba9a542a1d85f2dea_***_Alexander, Shaw
12b61893c794b14f11cf0a84cb947d0e_***_Jiaying, Zhang
5894777b8f9c6e64bde3568d68078d40_***_Michael, Friswell
author Mohammadreza, Amoozgar
Alexander, Shaw
Jiaying, Zhang
Michael, Friswell
author2 Mohammadreza Amoozgar
Alexander Shaw
Jiaying Zhang
Michael Friswell
format Journal article
container_title AIAA Journal
container_volume 57
container_issue 10
container_start_page 4218
publishDate 2019
institution Swansea University
issn 0001-1452
1533-385X
doi_str_mv 10.2514/1.j057591
publisher American Institute of Aeronautics and Astronautics (AIAA)
document_store_str 0
active_str 0
description In this paper, a new concept for morphing composite blades is proposed, and how this concept changes the twist distribution of the blade is explained. A change in the blade twist is obtained by adding a mass to the blade that produces an extra centrifugal force. This centrifugal force then may produce a moment that can change the blade twist via the extension–twist or bend–twist coupling of the composite lamination. These types of couplings are present in antisymmetrically and symmetrically laminated beams, respectively. The dynamics of the rotating composite blade is modeled by using the geometrically exact fully intrinsic beam equations. The concentrated mass is considered as a nonstructural concentrated mass that has offsets with respect to the beam reference line. The nonlinear partial differential equations are discretized by using a time–space scheme, the converged results are compared with those reported in the literature, and very good agreement is observed. It is found that, for an antisymmetric lamination, the spanwise location of the concentrated mass affects the twist, whereas in the symmetric case, the chordwise position of the concentrated mass is the source of twist change. It is also found that introducing the concentrated mass to a real blade can change the twist dramatically.
published_date 2019-10-01T04:18:51Z
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score 10.790515