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The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover / Mohammadreza Amoozgar; Alexander Shaw; Jiaying Zhang; Michael Friswell

Journal of Fluids and Structures, Volume: 87, Pages: 124 - 136

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

Abstract

In this paper, the aeroelastic stability of a composite hingeless rotor blade with a chordwise movable mass is investigated. The point mass is located near the tip of the blade and its chordwise location is variable with respect to the elastic axis and can be moved during the flight. This movable ma...

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Published in: Journal of Fluids and Structures
ISSN: 0889-9746
Published: 2019
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URI: https://cronfa.swan.ac.uk/Record/cronfa49881
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spelling 2019-07-17T09:40:40.5680075 v2 49881 2019-04-04 The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover 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 2019-04-04 In this paper, the aeroelastic stability of a composite hingeless rotor blade with a chordwise movable mass is investigated. The point mass is located near the tip of the blade and its chordwise location is variable with respect to the elastic axis and can be moved during the flight. This movable mass is added to the blade to actuate the blade twist during flight. By actuating the mass in the chord direction of the blade during the flight, a bending moment which is the result of the centrifugal force of the mass and its offset is induced on the blade. This bending moment induces twist in the blade, due to bend-twist coupling in the composite lamination. The blade is modelled by using the geometrically exact fully intrinsic beam equations along with the variational asymptotic beam sectional analysis. The aerodynamic loads are simulated by using the two-dimensional strip theory combined with a uniform inflow. The nonlinear partial differential aeroelastic equations are discretized by a time-space scheme, and the converged results are compared with those reported in the literature and a very good match is observed. The results show that by positioning the mass near the tip of the blade, and also by using the ply angle of about 30 degree in this configuration, the highest possible twist change is achieved when the mass moves from the leading edge to the trailing edge of the blade. Moreover, the spanwise location of the mass slightly changes the stability boundaries, while the chordwise movement significantly affects the aeroelastic instability. Journal Article Journal of Fluids and Structures 87 124 136 0889-9746 Morphing blade, Aeroelastic stability, Composite material, Bend-twist coupling, Fully intrinsic equations, Concentrated mass 31 5 2019 2019-05-31 10.1016/j.jfluidstructs.2019.03.017 COLLEGE NANME COLLEGE CODE Swansea University 2019-07-17T09:40:40.5680075 2019-04-04T08:58:09.1168986 Mohammadreza Amoozgar 1 Alexander Shaw 0000-0002-7521-827X 2 Jiaying Zhang 0000-0001-7308-5090 3 Michael Friswell 4 0049881-04042019155114.pdf amoozgar2019.pdf 2019-04-04T15:51:14.6130000 Output 1058521 application/pdf Accepted Manuscript true 2020-03-29T00:00:00.0000000 true eng
title The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
spellingShingle The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
Mohammadreza, Amoozgar
Alexander, Shaw
Jiaying, Zhang
Michael, Friswell
title_short The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
title_full The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
title_fullStr The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
title_full_unstemmed The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
title_sort The effect of a movable mass on the aeroelastic stability of composite hingeless rotor blades in hover
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 Journal of Fluids and Structures
container_volume 87
container_start_page 124
publishDate 2019
institution Swansea University
issn 0889-9746
doi_str_mv 10.1016/j.jfluidstructs.2019.03.017
document_store_str 1
active_str 0
description In this paper, the aeroelastic stability of a composite hingeless rotor blade with a chordwise movable mass is investigated. The point mass is located near the tip of the blade and its chordwise location is variable with respect to the elastic axis and can be moved during the flight. This movable mass is added to the blade to actuate the blade twist during flight. By actuating the mass in the chord direction of the blade during the flight, a bending moment which is the result of the centrifugal force of the mass and its offset is induced on the blade. This bending moment induces twist in the blade, due to bend-twist coupling in the composite lamination. The blade is modelled by using the geometrically exact fully intrinsic beam equations along with the variational asymptotic beam sectional analysis. The aerodynamic loads are simulated by using the two-dimensional strip theory combined with a uniform inflow. The nonlinear partial differential aeroelastic equations are discretized by a time-space scheme, and the converged results are compared with those reported in the literature and a very good match is observed. The results show that by positioning the mass near the tip of the blade, and also by using the ply angle of about 30 degree in this configuration, the highest possible twist change is achieved when the mass moves from the leading edge to the trailing edge of the blade. Moreover, the spanwise location of the mass slightly changes the stability boundaries, while the chordwise movement significantly affects the aeroelastic instability.
published_date 2019-05-31T04:10:40Z
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score 10.801289