The report presents the technical status of the rotor/wing concept of a stopped-rotor helicopter configuration. The configuration presents attractive performance characteristics for a high-speed VTOL aircraft. The ability to predict aerodynamic performance characteristics in all flight modes is substantiated by wind-tunnel tests. A major technical problem of 3-per-rev oscillating loads on the rotor/wing pylon was minimized by the effective use of cyclic blade pitch during the high-advance-ratio portion of conversion. High values of oscillating blade-root moments were recorded during testing of a dynamic model. It is not known if there is a schedule of cyclic pitch that will minimize both pylon loads and blade-root loads simultaneously. (Author)
Rotor/Wing
1970
79 pages
Report
Keine Angabe
Englisch
TIBKAT | 26.1992,11 - 49.2015,5
Rotor wing replaceable portable four-rotor wing aircraft
Europäisches Patentamt | 2015
|Rotor wing tilting mechanism, tilting rotor wing with rotor wing tilting mechanism and aircraft
Europäisches Patentamt | 2024
|Upper rotor wing control assembly and upper rotor wing
Europäisches Patentamt | 2023
|Folding rotor wing, aircraft and rotor wing control system
Europäisches Patentamt | 2023
|