Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps.
Low speed autogyro yaw control apparatus and method
2016-03-08
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Measurement of autogyro control forces
Online Contents | 1998
|Measurement of autogyro control forces
Tema Archive | 1998
|Engineering Index Backfile | 1934
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