Compact electromechanical actuator

• US 8,390,160 B2
• Filed: 01/14/2010
• Issued: 03/05/2013
• Est. Priority Date: 01/14/2010
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Gieras, Jacek F., Rozman, Gregory I.
• Primary Examiner(s): NGUYEN, HANH N
• Application Number:
  US12/687,152
• Publication Number:
  US 20110169357A1
• Time in Patent Office: 1,146 Days
• Field of Search: 310/83, 310/156.02
• US Class Current: 310/83
• CPC Class Codes: B64C 13/50 using electrical energy
• CPC Class Codes: H02K 21/145 having an annular armature coil with homopolar co-operation H02K21/20
• CPC Class Codes: H02K 21/227 having an annular armature coil
• CPC Class Codes: H02K 5/18 with ribs or fins for improving heat transfer
• CPC Class Codes: H02K 5/225 Terminal boxes or connection arrangements specially adapted for submersible motors H02K5/132
• CPC Class Codes: H02K 7/116 with gears
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An electromechanical actuator for controlling the position of an aircraft component has a linear actuator to be driven to position a component. A transverse flux motor drives the linear actuator to move in a linear direction and control the position of the component.

Claims

1. An electromechanical actuator for controlling the position of an aircraft component comprising:

a linear actuator to be driven to position a component;

a transverse flux motor driving said linear actuator to move in a linear direction and control the position of the component; and

said motor carries a redundant set of coils.

2. The system as set forth in claim 1, wherein a ball screw connection connects said motor to said linear actuator.

3. The system as set forth in claim 2, wherein said motor drives a first gear which engages and drives an output gear to in turn drive a rotating threaded member to move said ball screw, and move said linear actuator.

4. The system as set forth in claim 2, wherein said motor directly drives a threaded member to move said ball screw, and drive said linear actuator.

5. The system as set forth in claim 1, wherein there are three phases of redundant coils.

6. The system as set forth in claim 1, wherein said motor includes an internal stator having at least one coil.

7. The system as set forth in claim 1, wherein said motor has an external stator having at least one coil.

8. They system as set forth in claim 1, wherein said redundant set of coils provide fault tolerance.

9. An aircraft component and drive comprising:

an electromechanical actuator controlling the position of an aircraft component;

said electromechanical actuator including a linear actuator to position said component;

a transverse flux motor driving said linear actuator to move in a linear direction and control the position of said component; and

said motor carries a redundant set of coils.

10. The aircraft component as recited in claim 9, wherein a ball screw connection connects said motor to said linear actuator.

11. The aircraft component as recited in claim 9, wherein said motor includes an internal stator having at least one coil.

12. The aircraft component as recited in claim 9, wherein said motor has an external stator having at least one coil.

13. The aircraft component as recited in claim 9, wherein said motor is a three-phase motor, and there are redundant coils for each of said three-phases.

14. The aircraft component as recited in claim 9, wherein said component controls aerodynamic properties.

15. The aircraft component as recited in claim 9, wherein said redundant set of coils provide fault tolerance.