公开(公告)号：US20230278699A1

公开(公告)日：2023-09-07

申请号：US18118129

申请日：2023-03-06

Applicant: DASSAULT AVIATION

Inventor： Laurent PISTIAUX ,  Vincent MATEUS

IPC: B64C13/04

CPC classification number: B64C13/044 ,  B64C25/42

Abstract: An aircraft rudder pedal includes a frame, a pair of pedals, an output shaft and a mechanical kinematic chain for transmitting to the output shaft a displacement of at least one of the pedals relative to the frame. The mechanical kinematic chain comprises a central transmission part able to be rotated relative to the frame by a displacement of one of the pedals relative to the frame. The mechanical kinematic chain also includes a transmission mechanism joining the central transmission part to the output shaft. The transmission mechanism includes a homokinetic association of two universal joints between said central transmission part and the output shaft.

公开(公告)号：US20250026467A1

公开(公告)日：2025-01-23

申请号：US18907917

申请日：2024-10-07

Applicant: DASSAULT AVIATION

Inventor： Laurent PISTIAUX ,  Vincent MATEUS

IPC: B64C13/04 ,  B64C25/42

Abstract: An aircraft rudder pedal includes a frame, a pair of pedals, an output shaft and a mechanical kinematic chain for transmitting to the output shaft a displacement of at least one of the pedals relative to the frame. The mechanical kinematic chain comprises a central transmission part able to be rotated relative to the frame by a displacement of one of the pedals relative to the frame. The mechanical kinematic chain also includes a transmission mechanism joining the central transmission part to the output shaft. The transmission mechanism includes a homokinetic association of two universal joints between said central transmission part and the output shaft.

公开(公告)号：US20230278698A1

公开(公告)日：2023-09-07

申请号：US18118127

申请日：2023-03-06

Applicant: DASSAULT AVIATION

Inventor： Laurent PISTIAUX ,  Vincent MATEUS

IPC: B64C13/04 ,  B64C25/42 ,  B60T7/04

CPC classification number: B64C13/044 ,  B64C25/42 ,  B60T7/042

Abstract: An aircraft rudder pedal comprising a frame and at least one pedal side system. The or each pedal side system includes a pedal and an articulated support structure of the pedal connecting the pedal to the frame. The articulated support structure of said pedal comprises a crank, a lever and a support link. The crank presents a first pivotal articulation connection to the frame and a second pivotal articulation connection with the support link. The lever presents a first pivotal articulation connection with the frame and a second pivotal articulation connection with the support link.

公开(公告)号：US20230278697A1

公开(公告)日：2023-09-07

申请号：US18118125

申请日：2023-03-06

Applicant: DASSAULT AVIATION

Inventor： Eric GRANIER ,  Vincent MATEUS

IPC: B64C13/04 ,  B64C13/50 ,  B64C13/12 ,  B64C13/06

CPC classification number: B64C13/044 ,  B64C13/06 ,  B64C13/12 ,  B64C13/50

Abstract: An aircraft rudder pedal frame includes a base, a support framework and connection interfaces. Each connection interface is able to connect another part of the rudder pedal to the frame. The support framework connects each connection interface to the base. The support framework includes framework elements arranged in a lattice, at least one of the framework elements extending from each connection interface.