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:
Oct. 27, 2020

Filed:

Mar. 02, 2017
Applicant:

Lockheed Martin Corporation, Bethesda, MD (US);

Inventors:

Dustin E. Gamble, San Luis Obispo, CA (US);

Matthew Curran, Los Osos, CA (US);

Brian Miller, San Luis Obispo, CA (US);

Assignee:

Lockheed Martin Corporation, Bethesda, MD (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 27/39 (2006.01); B64C 27/48 (2006.01); B64C 27/50 (2006.01); B64C 27/10 (2006.01); B64C 39/02 (2006.01); B64C 17/04 (2006.01); B64C 27/52 (2006.01); B64C 25/32 (2006.01);
U.S. Cl.
CPC ...
B64C 27/39 (2013.01); B64C 17/04 (2013.01); B64C 27/10 (2013.01); B64C 27/48 (2013.01); B64C 27/50 (2013.01); B64C 27/52 (2013.01); B64C 39/024 (2013.01); B64C 2025/325 (2013.01); B64C 2201/024 (2013.01); B64C 2201/088 (2013.01); B64C 2201/108 (2013.01); B64C 2201/127 (2013.01); B64C 2201/165 (2013.01);
Abstract

A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.


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