In the present report, with the aid of the usual computation methods, a rotor is investigated the pitch of whose blades is capable of being controlled in such a manner that it varies linearly with the flapping angle. To test the effect of this linkage on the aircraft performance, the theory is applied to an illustrative example.
Aerodynamics of Rotating-wing Aircraft with Blade-pitch Control
01.02.1940
Sonstige
Keine Angabe
Englisch
Aerodynamics of rotating-wing aircraft with blade-pitch control
TIBKAT | 1940
|Aerodynamics of rotating-wing aircraft with bladepitch control
Engineering Index Backfile | 1940
|Contribution to aerodynamics of rotating wing aircraft
Engineering Index Backfile | 1941
|ROTARY-WING AIRCRAFT INDIVIDUAL ROTOR BLADE PITCH CONTROL SYSTEM
Europäisches Patentamt | 2024
|ROTARY-WING AIRCRAFT INDIVIDUAL ROTOR BLADE PITCH CONTROL SYSTEM
Europäisches Patentamt | 2022
|