Flexible matrix composite skins for One-dimensional wing morphing

Gabriel Murray, Farhan Gandhi, Charles Bakis

Research output: Contribution to journalArticle

55 Citations (Scopus)

Abstract

Morphing aircraft wings require flexible skins that undergo large strains, have low in-plane stiffness, and high out-of-plane stiffness to carry aerodynamic loads. For some morphing applications deformation and low stiffness in the flexskin is required in one direction. In these cases, a flexible matrix composite (FMC) skin is proposed as a possible solution. A FMC comprises of stiff fibers embedded in a soft, high-strain capable matrix material. The matrix-dominated direction is aligned with the morphing direction. This allows the skin to undergo large strain at low energy cost. However, the high-stiffness in the fiber-dominated direction allows application of pretension along this direction, without rupture, and is critical for the membrane skin to carry out-of-plane pressure loads without excessive deformation. An analysis for a FMC skin panel is developed and validated against experiment. The analysis is used to conduct design studies. Comparison of the FMC skin to a matrix-only skin illustrates the importance of the fiber's stiffness in tolerating pretension and limiting out-of-plane deformation under load. The other dominant parameter that limits out-of-plane deformation is panel size, with smaller lengths in the non-morphing direction proving beneficial. In general, fiber and matrix modulus has limited effect on out-of-plane deformation of flexskin panels.

Original languageEnglish (US)
Pages (from-to)1771-1781
Number of pages11
JournalJournal of Intelligent Material Systems and Structures
Volume21
Issue number17
DOIs
StatePublished - Nov 1 2010

Fingerprint

Skin
Composite materials
Stiffness
Fibers
Aerodynamic loads
Direction compound
Membranes
Costs
Experiments

All Science Journal Classification (ASJC) codes

  • Materials Science(all)
  • Mechanical Engineering

Cite this

@article{43b0b7df0bde4dd887fa061d33b98c81,
title = "Flexible matrix composite skins for One-dimensional wing morphing",
abstract = "Morphing aircraft wings require flexible skins that undergo large strains, have low in-plane stiffness, and high out-of-plane stiffness to carry aerodynamic loads. For some morphing applications deformation and low stiffness in the flexskin is required in one direction. In these cases, a flexible matrix composite (FMC) skin is proposed as a possible solution. A FMC comprises of stiff fibers embedded in a soft, high-strain capable matrix material. The matrix-dominated direction is aligned with the morphing direction. This allows the skin to undergo large strain at low energy cost. However, the high-stiffness in the fiber-dominated direction allows application of pretension along this direction, without rupture, and is critical for the membrane skin to carry out-of-plane pressure loads without excessive deformation. An analysis for a FMC skin panel is developed and validated against experiment. The analysis is used to conduct design studies. Comparison of the FMC skin to a matrix-only skin illustrates the importance of the fiber's stiffness in tolerating pretension and limiting out-of-plane deformation under load. The other dominant parameter that limits out-of-plane deformation is panel size, with smaller lengths in the non-morphing direction proving beneficial. In general, fiber and matrix modulus has limited effect on out-of-plane deformation of flexskin panels.",
author = "Gabriel Murray and Farhan Gandhi and Charles Bakis",
year = "2010",
month = "11",
day = "1",
doi = "10.1177/1045389X10369719",
language = "English (US)",
volume = "21",
pages = "1771--1781",
journal = "Journal of Intelligent Material Systems and Structures",
issn = "1045-389X",
publisher = "SAGE Publications Ltd",
number = "17",

}

Flexible matrix composite skins for One-dimensional wing morphing. / Murray, Gabriel; Gandhi, Farhan; Bakis, Charles.

In: Journal of Intelligent Material Systems and Structures, Vol. 21, No. 17, 01.11.2010, p. 1771-1781.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Flexible matrix composite skins for One-dimensional wing morphing

AU - Murray, Gabriel

AU - Gandhi, Farhan

AU - Bakis, Charles

PY - 2010/11/1

Y1 - 2010/11/1

N2 - Morphing aircraft wings require flexible skins that undergo large strains, have low in-plane stiffness, and high out-of-plane stiffness to carry aerodynamic loads. For some morphing applications deformation and low stiffness in the flexskin is required in one direction. In these cases, a flexible matrix composite (FMC) skin is proposed as a possible solution. A FMC comprises of stiff fibers embedded in a soft, high-strain capable matrix material. The matrix-dominated direction is aligned with the morphing direction. This allows the skin to undergo large strain at low energy cost. However, the high-stiffness in the fiber-dominated direction allows application of pretension along this direction, without rupture, and is critical for the membrane skin to carry out-of-plane pressure loads without excessive deformation. An analysis for a FMC skin panel is developed and validated against experiment. The analysis is used to conduct design studies. Comparison of the FMC skin to a matrix-only skin illustrates the importance of the fiber's stiffness in tolerating pretension and limiting out-of-plane deformation under load. The other dominant parameter that limits out-of-plane deformation is panel size, with smaller lengths in the non-morphing direction proving beneficial. In general, fiber and matrix modulus has limited effect on out-of-plane deformation of flexskin panels.

AB - Morphing aircraft wings require flexible skins that undergo large strains, have low in-plane stiffness, and high out-of-plane stiffness to carry aerodynamic loads. For some morphing applications deformation and low stiffness in the flexskin is required in one direction. In these cases, a flexible matrix composite (FMC) skin is proposed as a possible solution. A FMC comprises of stiff fibers embedded in a soft, high-strain capable matrix material. The matrix-dominated direction is aligned with the morphing direction. This allows the skin to undergo large strain at low energy cost. However, the high-stiffness in the fiber-dominated direction allows application of pretension along this direction, without rupture, and is critical for the membrane skin to carry out-of-plane pressure loads without excessive deformation. An analysis for a FMC skin panel is developed and validated against experiment. The analysis is used to conduct design studies. Comparison of the FMC skin to a matrix-only skin illustrates the importance of the fiber's stiffness in tolerating pretension and limiting out-of-plane deformation under load. The other dominant parameter that limits out-of-plane deformation is panel size, with smaller lengths in the non-morphing direction proving beneficial. In general, fiber and matrix modulus has limited effect on out-of-plane deformation of flexskin panels.

UR - http://www.scopus.com/inward/record.url?scp=78650365535&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=78650365535&partnerID=8YFLogxK

U2 - 10.1177/1045389X10369719

DO - 10.1177/1045389X10369719

M3 - Article

AN - SCOPUS:78650365535

VL - 21

SP - 1771

EP - 1781

JO - Journal of Intelligent Material Systems and Structures

JF - Journal of Intelligent Material Systems and Structures

SN - 1045-389X

IS - 17

ER -