Coupling for control of helicopter yaw push rod, esp. for helicopters whose rear boom is foldable as in case of helicopter carrying ships

The coupling (10) comprises two arms (11,12) which pivot opposite each other about an axis (A-A) on a structural beam (1) and about an axis (B-B) on the pivoting diverter (4). When the diverter is in alignment with the beam the two arm axes are identical. The arm (11) pivoted on the beam input push...

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Bibliographic Details
Main Authors GEMMATI BERNARD HENRI ALBERT, HOUSSAT DIDIER ERIC, LE BRAS CHRISTOPHE GUY NICOLAS
Format Patent
LanguageEnglish
French
Published 21.06.1996
Edition6
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Summary:The coupling (10) comprises two arms (11,12) which pivot opposite each other about an axis (A-A) on a structural beam (1) and about an axis (B-B) on the pivoting diverter (4). When the diverter is in alignment with the beam the two arm axes are identical. The arm (11) pivoted on the beam input push rod (8) has two support surfaces (21,22). These come into contact with one of the support surfaces (23,24) of the other arm (12) pivoted on the diverter output push rod (9) when the diverter and the beam are in alignment. Rotation of the input arm caused by translation of the input push rod causes rotation of the output arm and translation of the output push rod. Le dispositif (10) comprend deux bras (11, 12) pivotant en vis-à-vis sur la poutre de structure (1) et sur la dérive (4) pivotante, autour d'axes confondus lorsque la dérive (4) est alignée avec la poutre (1). Le bras (11), articulé sur une bielle d'entrée (8) sur la poutre (1), présente deux surfaces d'appui (21, 22) venant, lorsque la dérive (4) et la poutre (1) sont alignées, en contact chacune avec l'une des surfaces d'appui (23, 24) du bras (12) articulé sur une bielle de sortie (9) sur la dérive (4), pour transmettre les translations de la bielle (8) à la bielle (9) par rotation du bras (8) poussant le bras (9) en rotation.Application à la commande en lacet des hélicoptères à poutre arrière repliable.
Bibliography:Application Number: FR19940015322