Strength of composite sandwich panels containing debonds
A method for determining the critical debond size between the facesheet and the core in composite sandwich panels under in-plane compression is described. The approach uses fracture mechanics together with a buckling criterion for a debonded faceskin. The technique yields predictions for the critica...
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Published in | International journal of solids and structures Vol. 30; no. 2; pp. 211 - 223 |
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Main Authors | , , |
Format | Journal Article |
Language | English |
Published |
Oxford
Elsevier Ltd
1993
Elsevier Science |
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Abstract | A method for determining the critical debond size between the facesheet and the core in composite sandwich panels under in-plane compression is described. The approach uses fracture mechanics together with a buckling criterion for a debonded faceskin. The technique yields predictions for the critical in-plane compressive load for debond propagation as a function of core-to-faceskin debond size, faceskin thickness, lay-up, composite material properties, and honeycomb properties and geometries. A computer program, developed in this work, calculates the critical buckling load and facesheet deformed shape by solving an eigenvalue problem. An experimental study was conducted to determine the onset of delamination buckling in composite sandwich panels containing such flaws. Sandwich panel specimens of graphite/epoxy faceskins and aluminum honeycomb core were constructed with embedded delaminations and with varying faceskin thicknesses and core sizes. Four-point bending tests were conducted such that the faceskin containing the debond was under in-plane compression. The predicted critical fracture loads, computed using the proposed theoretical models which were solved using a numerical computational scheme, closely followed the experimental measurements. |
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AbstractList | A method for determining the critical debond size between the facesheet and the core in composite sandwich panels under in-plane compression is described. The approach uses fracture mechanics together with a buckling criterion for a debonded faceskin. The technique yields predictions for the critical in-plane compressive load for debond propagation as a function of core-to-faceskin debond size, faceskin thickness, lay-up, composite material properties, and honeycomb properties and geometries. A computer program developed calculates the critical buckling load and facesheet deformed shape by solving an eigenvalue problem. The onset of delamination buckling in composite sandwich panels containing such flaws is determined. Sandwich panel specimens of graphite/epoxy (T-300/934) faceskins and Al honeycomb core were constructed with embedded delaminations and with varying faceskin thicknesses and core sizes. Four-point bending tests were conducted such that the faceskin containing the debond was under in-plane compression. The predicted critical fracture loads, computed using the proposed theoretical models which were solved using a numerical computational scheme, closely followed the experimental measurements. A method for determining the critical debond size between the facesheet and the core in composite sandwich panels under in-plane compression is described. The approach uses fracture mechanics together with a buckling criterion for a debonded faceskin. The technique yields predictions for the critical in-plane compressive load for debond propagation as a function of core-to-faceskin debond size, faceskin thickness, lay-up, composite material properties, and honeycomb properties and geometries. A computer program, developed in this work, calculates the critical buckling load and facesheet deformed shape by solving an eigenvalue problem. An experimental study was conducted to determine the onset of delamination buckling in composite sandwich panels containing such flaws. Sandwich panel specimens of graphite/epoxy faceskins and aluminum honeycomb core were constructed with embedded delaminations and with varying faceskin thicknesses and core sizes. Four-point bending tests were conducted such that the faceskin containing the debond was under in-plane compression. The predicted critical fracture loads, computed using the proposed theoretical models which were solved using a numerical computational scheme, closely followed the experimental measurements. |
Author | Miller, T.C Dharan, C.K.H Kim, W.C |
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Cites_doi | 10.1177/002199838501900105 10.1016/0013-7944(86)90071-8 10.1115/1.3443485 10.1115/1.3166988 10.1520/CTR10168J 10.1177/002199838501900101 10.1177/002199838702101202 10.1017/S0001925900006028 10.1016/0013-7944(89)90145-8 10.1016/0020-7683(90)90043-U |
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Keywords | Compression Computer program Rupture Sandwich structure Experimental study Unsticking Buckling Composite material Strength Bending test |
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References | Carlsson, Pipes (BIB3) 1989 Vizzini, Lagace (BIB14) 1987; 21 Chai, Babcock (BIB5) 1985; 19 Hexcel Inc. (BIB8) 1984 Bruno, Grimaldi (BIB2) 1990; 26 Pearce, Webber (BIB12) 1972; 23 Kachanov (BIB9) 1988 Harris, Nordby (BIB7) 1969 Chai (BIB4) 1986; 24 Kim, Dharan (BIB10) 1989; 34 Shivakumar, Whitcomb (BIB13) 1985; 19 Whitcomb (BIB15) 1989; 11 (BIB11) 1988 Dharan (BIB6) 1978; 100 Bottega, Maewal (BIB1) 1983; 50 Bottega (10.1016/0020-7683(93)90061-B_BIB1) 1983; 50 Whitcomb (10.1016/0020-7683(93)90061-B_BIB15) 1989; 11 Pearce (10.1016/0020-7683(93)90061-B_BIB12) 1972; 23 Vizzini (10.1016/0020-7683(93)90061-B_BIB14) 1987; 21 (10.1016/0020-7683(93)90061-B_BIB11) 1988 Chai (10.1016/0020-7683(93)90061-B_BIB4) 1986; 24 Chai (10.1016/0020-7683(93)90061-B_BIB5) 1985; 19 Harris (10.1016/0020-7683(93)90061-B_BIB7) 1969 Kachanov (10.1016/0020-7683(93)90061-B_BIB9) 1988 Shivakumar (10.1016/0020-7683(93)90061-B_BIB13) 1985; 19 Bruno (10.1016/0020-7683(93)90061-B_BIB2) 1990; 26 Dharan (10.1016/0020-7683(93)90061-B_BIB6) 1978; 100 Carlsson (10.1016/0020-7683(93)90061-B_BIB3) 1989 Hexcel Inc. (10.1016/0020-7683(93)90061-B_BIB8) 1984 Kim (10.1016/0020-7683(93)90061-B_BIB10) 1989; 34 |
References_xml | – volume: 11 start-page: 154 year: 1989 end-page: 157 ident: BIB15 article-title: Comparison of full 3-d, thin-film 3-d, and thin-film plate analyses of a postbuckled embedded delamination publication-title: J. Compos. Technol. & Res. contributor: fullname: Whitcomb – year: 1984 ident: BIB8 publication-title: Mechanical Properties of Hexcel Honeycomb Materials. No. TSB 120 contributor: fullname: Hexcel Inc. – volume: 34 start-page: 305 year: 1989 end-page: 324 ident: BIB10 article-title: A fracture control plan for composite structures publication-title: Engng Fract. Mech. contributor: fullname: Dharan – volume: 21 start-page: 1106 year: 1987 end-page: 1117 ident: BIB14 article-title: The buckling of a delaminated sublaminate on an elastic foundation publication-title: J. Compos. 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Mater. doi: 10.1177/002199838702101202 contributor: fullname: Vizzini – volume: 23 start-page: 148 year: 1972 ident: 10.1016/0020-7683(93)90061-B_BIB12 article-title: Buckling of sandwich panels with laminated face plates publication-title: Aero. Q. doi: 10.1017/S0001925900006028 contributor: fullname: Pearce – volume: 34 start-page: 305 year: 1989 ident: 10.1016/0020-7683(93)90061-B_BIB10 article-title: A fracture control plan for composite structures publication-title: Engng Fract. Mech. doi: 10.1016/0013-7944(89)90145-8 contributor: fullname: Kim – year: 1988 ident: 10.1016/0020-7683(93)90061-B_BIB9 contributor: fullname: Kachanov – year: 1984 ident: 10.1016/0020-7683(93)90061-B_BIB8 publication-title: Mechanical Properties of Hexcel Honeycomb Materials. No. TSB 120 contributor: fullname: Hexcel Inc. – volume: 26 start-page: 313 year: 1990 ident: 10.1016/0020-7683(93)90061-B_BIB2 article-title: Delamination failure of layered composite plates loaded in compression publication-title: Int. J. Solids Structures doi: 10.1016/0020-7683(90)90043-U contributor: fullname: Bruno |
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Snippet | A method for determining the critical debond size between the facesheet and the core in composite sandwich panels under in-plane compression is described. The... |
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SubjectTerms | Exact sciences and technology Fracture mechanics (crack, fatigue, damage...) Fundamental areas of phenomenology (including applications) Physics Solid mechanics Structural and continuum mechanics |
Title | Strength of composite sandwich panels containing debonds |
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