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Development of a fatigue-life methodology for composite structures subjected to out-of-plane load components
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sumich, Mark Kedward, Keith T. |
| Copyright Year | 1991 |
| Description | The efforts to identify and implement a fatigue life methodology applicable to demonstrate delamination failures for use in certifying composite rotor blades are presented. The RSRA/X-Wing vehicle was a proof-of-concept stopped rotor aircraft configuration which used rotor blades primarily constructed of laminated carbon fiber. Delamination of the main spar during ground testing demonstrated that significant interlaminar stresses were produced. Analysis confirmed the presence of out-of-plane load components. The wear out (residual strength) methodology and the requirements for its implementation are discussed. |
| File Size | 1231364 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910009928 |
| Archival Resource Key | ark:/13960/t22c3xh4q |
| Language | English |
| Publisher Date | 1991-02-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Fatigue Life Rotor Blades Laminates Residual Strength Fatigue Tests Ground Tests Carbon Fibers Wear Failure Analysis Delaminating Composite Structures Aircraft Configurations Loads Forces 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 |
