Blade pitch control for main rotor of helicopter

The hydraulic actuating mechanism is used to set the pitch of the blades (8) of the main rotor of a helicopter. The hydraulic circuit includes a bypass valve (20) in addition to the first valve (34) in the hydraulic line (38A,B) between the working chambers (16,18) of the piston and cylinder assembl...

Full description

Saved in:
Bibliographic Details
Main Author SCHULLER, JOHANNES, 83620 FELDKIRCHEN-WESTERHAM, DE
Format Patent
LanguageEnglish
German
Published 19.09.1996
Edition6
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
Online AccessGet full text

Cover

More Information
Summary:The hydraulic actuating mechanism is used to set the pitch of the blades (8) of the main rotor of a helicopter. The hydraulic circuit includes a bypass valve (20) in addition to the first valve (34) in the hydraulic line (38A,B) between the working chambers (16,18) of the piston and cylinder assembly (2) connected (6) to a rotor blade. There is a servo control valve (10) connected to the cyclic pitch control lever (14). The system also includes a hydraulic pressure source which varies according to the rotational speed of the main rotor.
Bibliography:Application Number: DE1995105333