公开(公告)号：WO2019139654A1

公开(公告)日：2019-07-18

申请号：PCT/US2018/055361

申请日：2018-10-11

Applicant: THE BOEING COMPANY

Inventor： FOX, Michael Thomas ,  ROACH, Jeffrey Michael ,  HOWELL, Eric Anton

IPC: B64C9/02 ,  B64C13/34 ,  F16F7/10 ,  B64C13/40

CPC classification number: B64C9/02 ,  B64C13/34 ,  B64C13/40 ,  F16F7/1022 ,  F16F9/12 ,  F16F2232/06

Abstract: There is provided a dual rack and pinion rotational inerter system (500) for damping movement (694) of a flight control surface (122) of an aircraft (100). The system (500) has a flexible holding structure (506) disposed between the flight control surface (122) and a support structure (116) of the aircraft (100). The system (500) has a dual rack and pinion assembly (550) held by and between the flexible holding structure (506). The dual rack and pinion assembly (550) has a first rack (552a), a second rack (552b), and a pinion (596) engaged to and between the racks (552a, 552b). The system (500) has a first terminal (502) coupled to the first rack (552a) and coupled to the flight control surface (122), via a pivot element (127), and a second terminal (503) coupled to the second rack (552b), and coupled to the support structure (116). The system (500) has a pair of inertia wheels (660) adjacent the flexible holding structure (506). The system (500) has an axle element (612) inserted through the inertial wheels (660), the flexible holding structure (506), and the pinion (596).

公开(公告)号：WO2019139653A1

公开(公告)日：2019-07-18

申请号：PCT/US2018/055344

申请日：2018-10-11

Applicant: THE BOEING COMPANY

Inventor： FOX, Michael Thomas ,  ROACH, Jeffrey Michael ,  HOWELL, Eric Anton

IPC: B64C9/02 ,  F16F7/10 ,  F16F15/14 ,  F16F7/116 ,  F16F15/12 ,  F16F15/121 ,  B64C13/38 ,  B64C13/40

CPC classification number: B64C9/02 ,  B64C13/38 ,  B64C13/40 ,  F16F7/1022 ,  F16F15/1204 ,  F16F15/1216

Abstract: There is provided a translational inerter assembly (500) for damping movement (606) of a flight control surface (122) of an aircraft (100). The assembly (500) has a press fit element (510) fixedly disposed within a first end (502a) of the flight control surface (122) and rotatably movable with the flight control surface (122). The assembly (500) further has an inertia element (512) coupled to and installed in the press fit element (510). The assembly (500) further has a torsion bar (514) having a torsion bar first end (564a) coupled to and installed in the inertia element (512), and having a torsion bar second end (564b) fixedly attached to a support structure (116) of the aircraft (100). Rotation of the flight control surface (122) causes translational movement (604) of the inertia element (512), via the press fit element (510), along a hinge axis (126) of the flight control surface (122) and along the torsion bar (514), resulting in the translational inerter assembly (500) damping movement (606) of the flight control surface (122).