Power-assisted aircraft crank device, and an aircraft

Patent metadata

Field	Value
Publication number	US-11097833-B2
Application number	US-202016802941-A
Country	US
Kind code	B2
Filing date	Feb 27, 2020
Priority date	Feb 27, 2019
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

A crank device provided with an upstream lever and with a downstream lever. The crank device includes a phase shifter system connected to the upstream lever and to the downstream lever so that movement in rotation of the upstream lever about an axis of rotation induces movement in rotation of the downstream lever about the axis of rotation, the phase shifter system comprising a linear actuator mechanism carried by the upstream lever, the linear actuator mechanism having an outlet rod, the outlet rod having only one degree of freedom of movement in translation relative to the upstream lever, the outlet rod being connected via an outlet helical connection to the downstream lever so that movement in translation of the outlet rod generates movement in rotation of the downstream lever about the axis of rotation.

First claim

What is claimed is:

1. An aircraft crank device provided with an upstream lever and with a downstream lever,
wherein the crank device includes a phase shifter system connected to the upstream lever and to the downstream lever so that movement in rotation of the upstream lever about an axis of rotation induces movement in rotation of the downstream lever about the axis of rotation, the phase shifter system comprising a linear actuator mechanism carried by the upstream lever, the linear actuator mechanism having an outlet rod, the outlet rod having only one degree of freedom of movement in translation relative to the upstream lever, the outlet rod being connected via an outlet helical connection to the downstream lever so that movement in translation of the outlet rod generates movement in rotation of the downstream lever about the axis of rotation relative to the upstream lever.

2. The aircraft crank device according to claim 1 , wherein the linear actuator mechanism comprises a linear actuator provided with the outlet rod.

3. The aircraft crank device according to claim 1 , wherein the linear actuator mechanism further comprises an intermediate rotary actuator, the intermediate rotary actuator including an intermediate rod that is mounted to move in rotation, the intermediate rod being connected to the outlet rod via a system for transforming movement in rotation into movement in translation.

4. The aircraft crank device according to claim 3 , wherein the system for transforming movement in rotation into movement in translation includes an inlet helical connection.

5. The aircraft crank device according to claim 4 , wherein the inlet helical connection includes an intermediate nut that meshes with the intermediate rod, the intermediate nut being constrained in rotation with the upstream lever and being mounted to move in translation relative to the upstream lever, the intermediate nut being secured to the outlet rod.

6. The aircraft crank device according to claim 1 , wherein at least the outlet rod or an intermediate nut secured to the outlet rod is connected to the upstream lever via at least one connection that constrains the upstream lever and the outlet rod to rotate together about the axis of rotation.

7. The aircraft crank device according to claim 6 , wherein the at least one connection comprises a sliding connection including at least one spline channel, or a key.

8. The aircraft crank device according to claim 1 , wherein the outlet helical connection includes an outlet nut secured to the downstream lever, the outlet nut being provided with tapping that meshes with a complementary thread on the outlet rod.

9. The aircraft crank device according to claim 1 , wherein the outlet helical connection comprises an outlet helical groove and an outlet stud of complementary shape that is disposed at least in part in the outlet helical groove, the outlet helical groove being carried by the outlet rod and the outlet stud being carried by the downstream lever, or the outlet helical groove being carried by the downstream lever and the outlet stud being carried by the outlet rod.

10. The aircraft crank device according to claim 1 , wherein the crank device includes a general rotary actuator, the general rotary actuator comprising a general rotor that is secured to the upstream lever, the general rotary actuator further comprising a general body that is secured to a stationary support, the general rotor being mounted to move in rotation relative to the general body.

11. The aircraft crank device according to claim 1 , wherein the upstream lever includes an arm that extends radially from a hub, the hub being provided with a cavity, the linear actuator mechanism being arranged in the cavity at least in part.

12. The aircraft crank device according to claim 11 , wherein the crank device includes a general rotary actuator, the general rotary actuator comprising a general rotor that is secured to the upstream lever, the general rotary actuator further comprising a general body that is secured to a stationary support, the general rotor being mounted to move in rotation relative to the general body and wherein the general rotor is fastened to the hub, at least one rolling bearing system being interposed between the hub and the support.

13. The aircraft crank device according to claim 1 , wherein the upstream lever and the downstream lever each have a single degree of freedom, which single degree of freedom is a degree of freedom of movement in rotation about the axis of rotation.

14. The aircraft crank device according to claim 1 , wherein the aircraft crank device includes an autopilot computer configured to control the linear actuator mechanism directly or indirectly.

15. A control system provided with a control and with a mechanical member, the control being suitable for being operated by a pilot, and the mechanical member having a position controlled by the control, the control system comprising a linkage connecting the control to the mechanical member, wherein the linkage includes at least one aircraft crank device according to claim 1 .

16. An aircraft, wherein the aircraft includes at least one aircraft crank device according to claim 1 .

Assignees

• Airbus Helicopters

Inventors

• Honnorat Olivier

Classifications

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• B64C27/59

  mechanical · CPC title

• B64C13/50

  using electrical energy · CPC title

• B64C13/18

  using automatic pilot · CPC title

• B64C13/30 Primary

  using cable, chain, or rod mechanisms · CPC title