Rotor enables much higher speeds with conventional helicopter; penalty paid for this in form of hub pitching moments which have to be balanced out externally either by use of two rotors, offset CG, aerodynamic surfaces, or inclination of mechanical axis; equations developed for calculating blade elemental angle of attack, claimed to be superior to classic methods for design office purposes. (See also - v 26 n 309 Nov 1954 p 378-82)
High offset flapping pin rotor analysis
Aircraft Eng
Aircraft Engineering ; 27 , n 311
1955
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
High Offset Flapping Pin Rotor Analysis
Emerald Group Publishing | 1954
|Online Contents | 2008
NTIS | 1999
|Europäisches Patentamt | 2016
|Articulated main rotor hub with inwardly CF bearing and 3% flapping hinge offset
Europäisches Patentamt | 2019
|