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.
New design of hingeless helicopter rotor improves stability
1975-06-01
Sonstige
Keine Angabe
Englisch
Stability and control of hingeless rotor helicopter ground resonance
Tema Archiv | 1974
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Europäisches Patentamt | 2023
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