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An examination of impact damage in glass-phenolic and aluminum honeycomb core composite panels
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Nettles, A. T. Hodge, A. J. Lance, D. G. |
| Copyright Year | 1990 |
| Description | An examination of low velocity impact damage to glass-phenolic and aluminum core honeycomb sandwich panels with carbon-epoxy facesheets is presented. An instrumented drop weight impact test apparatus was utilized to inflict damage at energy ranges between 0.7 and 4.2 joules. Specimens were checked for extent of damage by cross sectional examination. The effect of core damage was assessed by subjecting impact-damaged beams to four-point bend tests. Skin-only specimens (facings not bonded to honeycomb) were also tested for comparison purposes. Results show that core buckling is the first damage mode, followed by delaminations in the facings, matrix cracking, and finally fiber breakage. The aluminum honeycomb panels exhibited a larger core damage zone and more facing delaminations than the glass-phenolic core, but could withstand more shear stress when damaged than the glass-phenolic core specimens. |
| File Size | 909724 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900018560 |
| Archival Resource Key | ark:/13960/t9576b44c |
| Language | English |
| Publisher Date | 1990-08-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Panels Honeycomb Cores Aluminum Phenolic Resins Impact Tests Sandwich Structures Glass Fiber Reinforced Plastics Drop Tests Bend Tests Delaminating Shear Stress Graphite-epoxy Composites Metal Matrix Composites Buckling Impact Damage Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
