Automatic flight control actuator systems

Patent metadata

Field	Value
Publication number	US-10106245-B2
Application number	US-201514886801-A
Country	US
Kind code	B2
Filing date	Oct 19, 2015
Priority date	Oct 19, 2015
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

Automatic flight control actuator systems are provided. In one example, the system includes a pilot input linkage that receives an input and a flight surface output linkage adapted to control a flight surface. The system also includes a strain wave gear including a flex spline coupled to one of the pilot input linkage and the flight surface output linkage. The strain wave gear further includes a circular spline coupled to the other of the flight surface output linkage and the pilot input linkage, and coupled to the flex spline such that the input from the pilot input linkage is transferred to the flight surface output linkage via the strain wave gear.

First claim

What is claimed is:

1. An automatic flight control actuator system, comprising:
a pilot input linkage that receives an input;
a flight surface output linkage adapted to control a flight surface;
a strain wave gear including a flex spline coupled to the flight surface output linkage, and a circular spline coupled to the pilot input linkage and coupled to the flex spline such that the input from the pilot input linkage is transferred to the flight surface output linkage via the strain wave gear, the strain wave gear comprising a wave generator including a wave generator input shaft coupled to a wave generator cam, the wave generator cam received within a bearing, the bearing coupled to the flex spline such that movement of the wave generator input shaft moves the flight surface output linkage relative to the pilot input linkage; and
a stability augmentation system including a first motor, the first motor coupled to the wave generator input shaft to drive the wave generator input shaft to move the flight surface output linkage independent of the pilot input linkage.

2. The automatic flight control actuator system of claim 1 , wherein the stability augmentation system includes a second motor, the second motor coupled to the wave generator input shaft to drive the wave generator input shaft to move the flight surface output linkage independent of the pilot input linkage.

3. The automatic flight control actuator system of claim 1 , wherein the circular spline further comprises a hub and a trim input system is coupled to the hub to move the hub to adjust the pilot input linkage.

4. The automatic flight control actuator system of claim 3 , wherein the hub includes a first gear, and the trim input system includes a gear meshingly engaged with the first gear of the hub to move the hub.

5. The automatic flight control actuator system of claim 3 , wherein the trim input system includes a feel spring coupled to the hub and a portion of the trim input system, the feel spring movable by the trim input system such that the movement of the feel spring by the trim input system moves the hub.

6. The automatic flight control actuator system of claim 5 , wherein the trim input system comprises a trim motor coupled to a clutch, the clutch including a driving shaft driven by the trim motor and a driven shaft, the driven shaft coupled to a gear and the feel spring is coupled to the gear to be movable by the trim motor.

7. The automatic flight control actuator system of claim 3 , wherein the trim input system comprises a trim motor, which is coupled to a feel spring via a clutch, and the feel spring is coupled about a driven shaft of the clutch.

8. The automatic flight control actuator system of claim 1 , wherein the first motor of the stability augmentation system is coupled to the wave generator input shaft via a differential gear.

9. The automatic flight control actuator system of claim 1 , wherein the flex spline includes a housing coupled to a drive shaft, with the housing coupled to the circular spline and the drive shaft coupled to the flight surface output linkage.

10. The automatic flight control actuator system of claim 1 , wherein the flight surface output linkage is coupled to a swashplate.

11. An automatic flight control actuator system, comprising:
a pilot input linkage that receives an input;
a flight surface output linkage adapted to control a flight surface;
a stability augmentation system for moving the flight surface output linkage; and
a strain wave gear including a flex spline coupled to the flight surface output linkage, a circular spline coupled to the pilot input linkage and a wave generator coupled to the stability augmentation system, with the circular spline coupled to the flex spline such that the input from the pilot input linkage is transferred to the flight surface output linkage and the stability augmentation system drives the wave generator to move the flight surface output linkage independent of the input from the pilot input linkage.

12. The automatic flight control actuator system of claim 11 , wherein the wave generator further comprises a wave generator input shaft driven by the stability augmentation system, the wave generator input shaft coupled to a wave generator cam received within a bearing, the bearing coupled to the flex spline such that movement of the wave generator input shaft by the stability augmentation system moves the flight surface output linkage.

13. The automatic flight control actuator system of claim 12 , wherein the stability augmentation system includes a first motor and a second motor, and each of the first motor and the second motor are coupled to the wave generator input shaft to drive the wave generator input shaft to move the flight surface output linkage independent of the pilot input linkage.

14. The automatic flight control actuator system of claim 11 , wherein the circular spline further comprises a hub and a trim input system is coupled to the hub to move the hub to adjust the pilot input linkage.

15. The automatic flight control actuator system of claim 14 , wherein the hub includes a first gear, and the trim input system includes a gear meshingly engaged with the hub to move the hub.

16. The automatic flight control actuator system of claim 14 , wherein the trim input system includes a trim motor and a feel spring coupled to the hub and a portion of the trim input system, the trim motor coupled to the feel spring via a clutch, and the feel spring is coupled about a driven shaft of the clutch, the feel spring movable by the trim input system such that the movement of the feel spring by the trim input system moves the hub.

17. The automatic flight control actuator system of claim 13 , wherein the first motor of the stability augmentation system is coupled to the wave generator input shaft via a differential gear.

Assignees

• Honeywell Int Inc

Inventors

• Wilkens Dean

Classifications

• B64C27/605

  including swash plate, spider or cam mechanisms · CPC title

• B64C13/507

  with artificial feel · CPC title

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/18 Primary

  using automatic pilot · CPC title

• B64C13/345

  with artificial feel · CPC title