| File - Multifidelity design of stiffened composite panel with a crack.pdf | ||||||||
| Description | ||||||||
| In designing an aircraft composite fuselage and wing panels, one of the most important concerns is crack propagation in the skin of the stiffened panel. This study attempts to solve the weight optimization problem of a stiffened composite panel, subjected to crack propagation constraints, using two optimization strategies to satisfy the crack propagation requirements. |
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| Downloads | Views | Developer | Last Update | Version | Size | Type | Rank | |
| 0 | 15 | admin | Mar 08, 2010 - 22:40 | 52.2KB | No Votes, out of 0 Votes. | |||
| File Hash | ||||||||
| MD5: d782e36ef03834e56bf4ea7b3fea4283 · SHA1: ce98b5c0007a7e8152c21918135c7d494ffa4614 | ||||||||
| Download Time | ||||||||
| 56Kbit Modem: 8s · 256Kbit: 2s · 1Mbit: 1s · 5Mbit: 1s | ||||||||
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