公开(公告)号：US20170320565A1

公开(公告)日：2017-11-09

申请号：US15447845

申请日：2017-03-02

Applicant: Lockheed Martin Corporation

Inventor： DUSTIN E. GAMBLE ,  Matthew Curran ,  Brian Miller

IPC: B64C27/39 ,  B64C27/10 ,  B64C39/02 ,  B64C27/48 ,  B64C27/50

CPC classification number: B64C27/39 ,  B64C17/04 ,  B64C27/10 ,  B64C27/48 ,  B64C27/50 ,  B64C27/52 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/165

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.

公开(公告)号：US10814968B2

公开(公告)日：2020-10-27

申请号：US15447845

申请日：2017-03-02

Applicant: Lockheed Martin Corporation

Inventor： Dustin E. Gamble ,  Matthew Curran ,  Brian Miller

IPC: B64C27/39 ,  B64C27/48 ,  B64C27/50 ,  B64C27/10 ,  B64C39/02 ,  B64C17/04 ,  B64C27/52 ,  B64C25/32

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.