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| 003 | MiAaHDL | ||
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| 008 | 220427s1996 ohua t f000 0 eng d | ||
| 035 | ⊔ | ⊔ | ‡a(MiU)99187625264506381 |
| 035 | ⊔ | ⊔ | ‡asdr-miu.99187625264506381 |
| 035 | ⊔ | ⊔ | ‡a(OCoLC)1312742690 |
| 035 | ⊔ | ⊔ | ‡a(GWLA)gwla on1312742690 |
| 040 | ⊔ | ⊔ | ‡aTRAAL ‡beng ‡erda ‡cTRAAL |
| 049 | ⊔ | ⊔ | ‡aMAIN |
| 086 | 0 | ⊔ | ‡aD 301.45/57: 97-3045 |
| 100 | 1 | ⊔ | ‡aPipkins, Daniel S., ‡eauthor. |
| 245 | 1 | 0 | ‡aBUCKDEL v 0.9 users and theory manuals : ‡bbuckling and delamination analysis of stiffened laminated plates / ‡cD.S. Pipkins, S.N. Atluri. |
| 264 | ⊔ | 1 | ‡aWright-Patterson Air Force Base, Ohio : ‡bFlight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force, ‡c1996. |
| 300 | ⊔ | ⊔ | ‡a50 pages : ‡billustrations ; ‡c28 cm. |
| 336 | ⊔ | ⊔ | ‡atext ‡btxt ‡2rdacontent |
| 337 | ⊔ | ⊔ | ‡aunmediated ‡bn ‡2rdamedia |
| 338 | ⊔ | ⊔ | ‡avolume ‡bnc ‡2rdacarrier |
| 490 | 0 | ⊔ | ‡aAFWAL-TR (Air Force Wright Aeronautical Laboratories) ; ‡v97-3045 |
| 500 | ⊔ | ⊔ | ‡a"Final report for the period September 1995 - March 1996." |
| 500 | ⊔ | ⊔ | ‡a"April 1996." |
| 520 | ⊔ | ⊔ | ‡aBUCKDEL, performs geometrically nonlinear analysis of stiffened laminated composite plates with and without delaminations. BUCKDEL allows the user to perform: a linear static solution; a linear buckling (eigenvalue) analysis; and a nonlinear post-buckling analysis through both limit and bifurcation points. There are two finite elements in BUCKDEL; a quasi-conforming triangular laminated plate element based on a refined first order shear theory with seven degrees of freedom per node and a fiber reinforced beam element with seven degrees of freedom per node. The behavior of all materials is assumed to be linearly elastic. The multi-domain modeling method is used for the analysis of laminated plates containing delaminations. In this model, the delaminate, base and the undelaminate are modeled as 3 distinct. On the delamination front, Mindlin's deformation assumption is applied to obtain the relationship between the displacements in the delaminate, base and undelaminate. |
| 536 | ⊔ | ⊔ | ‡aResearch supported by the United States Air Force Flight Dynamics Directorate, and performed by Knowledge Systems, Inc., Forsyth, Georgia, under Contract No. ‡bF33615-95-C-3226. |
| 538 | ⊔ | ⊔ | ‡aMode of access: Internet. |
| 650 | ⊔ | 0 | ‡aComposite materials ‡xDelamination. |
| 650 | ⊔ | 0 | ‡aBuckling (Mechanics) |
| 700 | 1 | ⊔ | ‡aAtluri, Satya N., ‡eauthor. |
| 710 | 2 | ⊔ | ‡aWright Laboratory (Wright-Patterson Air Force Base, Ohio), ‡eissuing body. |
| 730 | 0 | ⊔ | ‡aTechnical Report Archive & Image Library (TRAIL) |
| 899 | ⊔ | ⊔ | ‡a39015104975704 |
| CID | ⊔ | ⊔ | ‡a102892571 |
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| DAT | 2 | ⊔ | ‡a2024-07-31T17:30:01Z |
| CAT | ⊔ | ⊔ | ‡aSDR-MIU ‡cmiu ‡dALMA ‡lprepare.pl-004-008 |
| FMT | ⊔ | ⊔ | ‡aBK |
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