The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
May. 19, 2020

Filed:

Feb. 27, 2018
Applicant:

Airbus Helicopters Deutschland Gmbh, Donauworth, DE;

Inventors:

Julius Vogl, Gersthofen, DE;

Gerald Kuntze-Fechner, Gmund am Tegernsee, DE;

Victoria Otto, Aix en Provence, FR;

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64C 11/32 (2006.01); B64C 27/605 (2006.01); B64C 27/78 (2006.01); B64C 27/72 (2006.01); B64C 27/82 (2006.01);
U.S. Cl.
CPC ...
B64C 11/32 (2013.01); B64C 27/605 (2013.01); B64C 27/72 (2013.01); B64C 27/78 (2013.01); B64C 27/82 (2013.01); B64C 2027/8254 (2013.01); Y02T 50/34 (2013.01);
Abstract

A pitch control device for a ducted tail rotor of a rotorcraft. The pitch control device comprises a control input member with a disc-shaped central component and at least two connecting arms that extend radially from the disc-shaped central component, wherein the disc-shaped central component is provided for being mounted to an associated pitch control shaft of the ducted tail rotor, and a control transfer member with a ring-shaped connector and at least two push rods that extend axially from the ring-shaped connector, wherein each one of the at least two push rods is provided for being coupled to an associated pitch lever of a rotor blade of the ducted tail rotor.


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