Compact electromechanical actuator
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.
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.