Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring

Amoozgar, Mohammadreza; Shaw, Alexander; Zhang, Jiaying; Friswell, Michael

doi:10.2514/1.j057591

Journal article 962 views

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
Online Access:	Check full text
URI:	https://cronfa.swan.ac.uk/Record/cronfa53415
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first_indexed	2020-02-03T19:23:29Z
last_indexed	2023-01-11T14:30:59Z
id	cronfa53415
recordtype	SURis
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spelling	2022-11-15T16:15:17.2960420 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 EEN 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 Engineering COLLEGE CODE EEN Swansea University 2022-11-15T16:15:17.2960420 2020-02-03T15:30:06.2290383 Faculty of Science and Engineering School of Engineering and Applied Sciences - Uncategorised 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)
college_str	Faculty of Science and Engineering
hierarchytype
hierarchy_top_id	facultyofscienceandengineering
hierarchy_top_title	Faculty of Science and Engineering
hierarchy_parent_id	facultyofscienceandengineering
hierarchy_parent_title	Faculty of Science and Engineering
department_str	School of Engineering and Applied Sciences - Uncategorised{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Engineering and Applied Sciences - Uncategorised
document_store_str	0
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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	2019-10-01T04:06:21Z
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score	11.037581

Composite Blade Twist Modification by Using a Moving Mass and Stiffness Tailoring

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