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Conference Paper/Proceeding/Abstract 1473 views

Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing

Alexander Shaw Orcid Logo

ICAST 2014

Swansea University Author: Alexander Shaw Orcid Logo

Abstract

Span morphing is potentially one of the most advantageous forms of morphing, because it can allow a wing to have high aspect ratio at low speed when induced drag is critical, or to have lower aspect ratio at high speed when skin drag or structural loads can become design constraints. However it rema...

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Published in: ICAST 2014
Published: The Hague, Netherlands 2014
URI: https://cronfa.swan.ac.uk/Record/cronfa24899
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spelling 2015-11-27T10:22:51.7589262 v2 24899 2015-11-27 Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing 10cb5f545bc146fba9a542a1d85f2dea 0000-0002-7521-827X Alexander Shaw Alexander Shaw true false 2015-11-27 AERO Span morphing is potentially one of the most advantageous forms of morphing, because it can allow a wing to have high aspect ratio at low speed when induced drag is critical, or to have lower aspect ratio at high speed when skin drag or structural loads can become design constraints. However it remains one of the harder forms of morphing to achieve without an excessive weight penalty, because of the requirement to add mechanisms to the wing box. Furthermore, the large changes in dimensions that are needed to make span morphing worthwhile mean that the wing skins used must be capable of handling large deformations. The ADaptive Aspect Ratio (ADAR) wing is a span-morph concept that features an Elastomeric Matrix Composite (EMC) skin in order to accommodate these large deformations. The EMC skin is an elastomeric material reinforced with fibers in the chordwise direction to suppress the in-plane Poisson ratio, which would otherwise lead to significant unwanted out-of-plane deformations in the final structure. The design of this skin is critical to the success of the ADAR wing, because there is a direct trade-off between the requirement for low deflections in response to aerodynamic loads, and the need to keep actuation forces as low as possible, to minimize the weight and power consumption of the actuators. The first requirement motivates a thick, stiff, and highly pre-stretched skin whereas the second motivates towards a thin, compliant membrane with minimal initial tension. This describes work towards a hyperelastic model of the material in an FE analysis of the structure, using a realistic section geometry and pressure distribution to estimate the deformation. The material model is validated with experimental data from sample material specimens. It is shown that the deformation of an elastomeric skin of this kind is very small under aerodynamic loading, and that therefore there is little aerodynamic penalty when using this type of wing. Conference Paper/Proceeding/Abstract ICAST 2014 The Hague, Netherlands elastomeric composite, morphing 6 10 2014 2014-10-06 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University 2015-11-27T10:22:51.7589262 2015-11-27T10:22:23.9125692 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering Alexander Shaw 0000-0002-7521-827X 1
title Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
spellingShingle Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
Alexander Shaw
title_short Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
title_full Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
title_fullStr Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
title_full_unstemmed Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
title_sort Modelling of an Elastomeric Composite Skin for a span-morphing aircraft wing
author_id_str_mv 10cb5f545bc146fba9a542a1d85f2dea
author_id_fullname_str_mv 10cb5f545bc146fba9a542a1d85f2dea_***_Alexander Shaw
author Alexander Shaw
author2 Alexander Shaw
format Conference Paper/Proceeding/Abstract
container_title ICAST 2014
publishDate 2014
institution Swansea University
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 Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 0
active_str 0
description Span morphing is potentially one of the most advantageous forms of morphing, because it can allow a wing to have high aspect ratio at low speed when induced drag is critical, or to have lower aspect ratio at high speed when skin drag or structural loads can become design constraints. However it remains one of the harder forms of morphing to achieve without an excessive weight penalty, because of the requirement to add mechanisms to the wing box. Furthermore, the large changes in dimensions that are needed to make span morphing worthwhile mean that the wing skins used must be capable of handling large deformations. The ADaptive Aspect Ratio (ADAR) wing is a span-morph concept that features an Elastomeric Matrix Composite (EMC) skin in order to accommodate these large deformations. The EMC skin is an elastomeric material reinforced with fibers in the chordwise direction to suppress the in-plane Poisson ratio, which would otherwise lead to significant unwanted out-of-plane deformations in the final structure. The design of this skin is critical to the success of the ADAR wing, because there is a direct trade-off between the requirement for low deflections in response to aerodynamic loads, and the need to keep actuation forces as low as possible, to minimize the weight and power consumption of the actuators. The first requirement motivates a thick, stiff, and highly pre-stretched skin whereas the second motivates towards a thin, compliant membrane with minimal initial tension. This describes work towards a hyperelastic model of the material in an FE analysis of the structure, using a realistic section geometry and pressure distribution to estimate the deformation. The material model is validated with experimental data from sample material specimens. It is shown that the deformation of an elastomeric skin of this kind is very small under aerodynamic loading, and that therefore there is little aerodynamic penalty when using this type of wing.
published_date 2014-10-06T03:29:34Z
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score 11.013731

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