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New design of hingeless helicopter rotor improves stability
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Bousman, W. G. Ormiston, R. A. Hodges, D. H. Peters, D. A. |
| Copyright Year | 1975 |
| Description | Cantilever blades are attached directly to rotor hub, thereby substantially reducing cost and complexity and increasing reliability of helicopter rotor. Combination of structural flap-lag coupling and pitch-lag coupling provides damping of 6 to 10%, depending on magnitude of coupling parameters. |
| File Size | 95398 |
| Page Count | 1 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750000132 |
| Archival Resource Key | ark:/13960/t98679190 |
| Language | English |
| Publisher Date | 1975-06-01 |
| Access Restriction | Open |
| Subject Keyword | Damping Bending Rotor Aerodynamics Helicopter Design Leading Edges Rotary Wings Pitch Inclination Time Lag Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |