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Aircraft fatigue and crack growth considering loads by structural component
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Yost, J. D. |
| Copyright Year | 1994 |
| Description | The indisputable 1968 C-130 fatigue/crack growth data is reviewed to obtain additional useful information on fatigue and crack growth. The proven Load Environment Model concept derived empirically from F-105D multichannel recorder data is refined to a simpler method by going from 8 to 5 variables in the spectra without a decrease in accuracy. This approach provides the true fatigue/crack growth and load environment by structural component for both fatigue and strength design. Methods are presented for defining fatigue scatter and damage at crack initiation. These design tools and criteria may be used for both metal and composite aircraft structure. |
| File Size | 786312 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950013081 |
| Archival Resource Key | ark:/13960/t6644p249 |
| Language | English |
| Publisher Date | 1994-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Composite Materials Refining Fatigue Materials Environment Models Composite Structures Aircraft Structures Loads Forces Crack Initiation Crack Propagation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
