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Shock adhesion test for composite bonded assembly using a high pulsed power generator
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10.1063/1.4811696
/content/aip/journal/jap/114/1/10.1063/1.4811696
http://aip.metastore.ingenta.com/content/aip/journal/jap/114/1/10.1063/1.4811696

Figures

Image of FIG. 1.
FIG. 1.

(a) Electromagnetic cell of the GEPI device (upper cell) and (b) normalized current shape and incident pressure.

Image of FIG. 2.
FIG. 2.

Experimental set-up of the load region (scale not respected).

Image of FIG. 3.
FIG. 3.

Comparison between experimental and computed velocity at the Aluminum/PMMA interface ( simulation, mesh size 10 m, step time 2 ns).

Image of FIG. 4.
FIG. 4.

Microscopic transverse observation of the 8 plies sample A after a load of 335 MPa. The loading zone is indicated by the white arrows.

Image of FIG. 5.
FIG. 5.

Numerical simulation of the wave propagation within an 8 plies laminate. The incident peak pressure was 335 MPa for sample A without damage. (a) Space-time diagram, compression in red, tensile stress in blue and (b) corresponding experimental and computed free surface velocity ( simulation, mesh size 2 m, step time 2 ns).

Image of FIG. 6.
FIG. 6.

Microscopic transverse observations with high magnification of the damage of 8 plies laminates. The incident peak pressure was: (a) 387 MPa sample B, (b) 521 MPa sample C, and (c) 759 MPa sample D. The loading zone is indicated by the arrows.

Image of FIG. 7.
FIG. 7.

Numerical simulation of the wave propagation within an 8 plies laminate using a cut-off criterion. The incident peak pressure was 387 MPa for sample B. (a) Space-time diagram with induced delamination, and (b) experimental and computed free surface velocity.

Image of FIG. 8.
FIG. 8.

Microscopic transverse observation of the assembly E bonded with EA9394 after a load of 455 MPa. The loading zone is indicated by the arrows.

Image of FIG. 9.
FIG. 9.

Numerical simulation of the wave propagation within a composite assembly bonded with EA9394. The incident peak pressure was 445 MPa for sample E without debonding. (a) Space-time diagram and (b) experimental and computed free surface velocity (mesh size 2 m, step time 2 ns).

Image of FIG. 10.
FIG. 10.

Microscopic observations of the fracture of the assembly F bonded with EA9394 after a 623 MPa load: (a) planar observations and (b) transverse observation of the reconstituted sample. The loading zone is indicated by the arrows.

Image of FIG. 11.
FIG. 11.

Numerical simulation of the wave propagation within a composite assembly bonded with EA9394 using a cut-off criterion. The incident peak pressure was 623 MPa for sample F. (a) Space-time diagram with induced debonding and (b) experimental and computed free surface velocity.

Image of FIG. 12.
FIG. 12.

Free surface velocity recorded on the assemblies bonded with EA9394 and FM73 submitted to a load of 0.85 GPa.

Image of FIG. 13.
FIG. 13.

Microscopic transverse observations of composite assemblies after a load of 0.85 GPa. The samples have been bonded using: (a) EA9394, reconstituted sample G, and (b) FM73, sample H. The loading zone is indicated by the arrows.

Tables

Generic image for table
Table I.

Parameters of the experiments performed on the GEPI device. The thicknesses are given starting with the loaded layer.

Generic image for table
Table II.

Material properties (T for transverse, i.e., through-thickness, L for longitudinal direction) ( ).

Generic image for table
Table III.

Debonding threshold of the specimens.

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/content/aip/journal/jap/114/1/10.1063/1.4811696
2013-07-01
2014-04-18
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752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: Shock adhesion test for composite bonded assembly using a high pulsed power generator
http://aip.metastore.ingenta.com/content/aip/journal/jap/114/1/10.1063/1.4811696
10.1063/1.4811696
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