BIDIRECTIONAL AIRCRAFT ROTOR

A bidirectional aircraft rotor for a rotorcraft tail rotor (301). The rotorcraft tail rotor uses a hub (121) and a first tail rotor blade (423) affixed to the hub (121). A pitch of the first tail rotor blade (423) is fixed, and a profile of a leading edge (203, 303) of the first tail rotor blade (42...

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Bibliographic Details
Main Authors HALDEMAN, Andrew Paul, ACEE, Aaron Alexander
Format Patent
LanguageEnglish
French
German
Published 06.05.2020
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
MARINE PROPULSION OR STEERING
PERFORMING OPERATIONS
RELATED EQUIPMENT
SHIPS OR OTHER WATERBORNE VESSELS
TRANSPORTING
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Summary:A bidirectional aircraft rotor for a rotorcraft tail rotor (301). The rotorcraft tail rotor uses a hub (121) and a first tail rotor blade (423) affixed to the hub (121). A pitch of the first tail rotor blade (423) is fixed, and a profile of a leading edge (203, 303) of the first tail rotor blade (423) is identical to a profile of a trailing edge (205, 305) of the first tail rotor blade (423). The tail rotor is driven by a torque source, such as an electric motor or an engine. The tail rotor uses variable RPM and reversible rotational direction to provide rotorcraft with yaw control.
Bibliography:Application Number: EP20180212490