【発明の名称】可変直径形ロータブレード作動システム

Japanese Patent JP2002532340

A

A rotor blade actuation system is disclosed for controlling extension and retraction of an outboard blade section of a rotor blade by varying the speed and direction of rotation between a main rotor shaft and a blade actuation shaft. The rotor blade actuation system includes a drive gear on the main rotor shaft and a blade actuation drive gear on the blade actuation drive shaft. A primary drive unit is engaged with and transmits rotary motion from the main rotor shaft to the blade actuation shaft. The primary drive unit includes an input gear engaged with the drive gear. A primary drive is engaged with the drive gear through an input gear and a master clutch. An output drive is engaged with the blade actuation drive gear. A forward clutch controls engagement of a forward planetary gearset with the primary drive and the output drive. The engagement of the forward planetary gearset causes the blade actuation shaft to rotate in the same direction as the rotation of the main rotor shaft. A reverse clutch controls engagement of a reverse planetary gearset with the primary drive and the output drive. The engagement of the reverse planetary gearset with the primary drive and the output drive causes the blade actuation shaft to rotate in the opposite direction from the rotation of the main rotor shaft. A rotor blade actuation control unit controls engagement and disengagement of the forward and reverse clutches.

WO/2019/156724	TOROIDAL PROPELLER
WO/2023/275516	DUCT ARRANGEMENT AND METHOD
JP2023139335	CONTROL DEVICE

Hager, Lee N.
Fitzpatrick, Paulsea.

JP2000589399A

October 02, 2002

December 14, 1999

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Sikorsky Aircraft Corporation

B64C11/00; B64C27/72; B64C27/58; B64C29/00; F03D1/06; (IPC1-7): B64C27/58; B64C29/00

Fujiya Shiga (2 outside)

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