Claims
- 1. A method for providing improved reliability in an aircraft door flight lock actuator comprising:
storing energy in a mechanical energy storage means and an electrical energy storage means; powering the actuator using the energy stored in the mechanical energy storage means and the electrical energy storage means to complete an unlocking stroke in the absence of aircraft power; and controlling a linear velocity of the actuator.
- 2. The method defined in claim 1, wherein storing energy in the mechanical energy storage means comprises deforming a compression coil spring during a powered locking stroke of the actuator.
- 3. The method defined in claim 1, wherein storing energy in the electrical energy storage means comprises charging at least one capacitor during a powered locking stroke of the actuator, and during a subsequent powered stall of the actuator.
- 4. The method defined in claim 1, wherein storing energy in the electrical energy storage means comprises charging a rechargeable battery during a powered locking stroke of the actuator, and during a subsequent powered stall of the actuator.
- 5. The method defined in claim 1, wherein the mechanical energy storage means and the electrical energy storage means are fully redundant.
- 6. The method defined in claim 1, wherein controlling the linear velocity of the actuator comprises:
sensing a rotational speed of an actuator motor; sensing a first current supplied to the motor; reducing the first current if the rotational speed is higher than a maximum speed, or if the first current is higher than a maximum current.
- 7. The method defined in claim 6, wherein controlling the linear velocity of the actuator further comprises:
shunting a second current generated by the motor into a damper circuit to place an electrical load on the motor if the first current is substantially zero and the rotational speed is higher than the maximum speed.
- 8. The method defined in claim 6, wherein sensing the rotational speed of the motor comprises measuring a frequency of a Hall effect sensor signal.
- 9. The method defined in claim 6, wherein sensing the rotational speed of the motor comprises measuring a back electromotive force generated by the motor.
- 10. The method defined in claim 6, wherein reducing the first current comprises reducing a voltage supplied to the motor.
- 11. The method defined in claim 6, wherein reducing the first current comprises pulse-width-modulating a power signal supplied to the motor.
- 12. A system for providing improved reliability in an aircraft door flight lock actuator comprising apparatus for:
storing energy in a mechanical energy storage means and an electrical energy storage means; powering the actuator using the energy stored in the mechanical energy storage means and the electrical energy storage means to complete an unlocking stroke in the absence of aircraft power; and controlling a linear velocity of the actuator.
- 13. The system defined in claim 12, wherein the apparatus for storing energy in the mechanical energy storage means comprises apparatus for deforming a compression coil spring during a powered locking stroke of the actuator.
- 14. The system defined in claim 12, wherein the apparatus for storing energy in the electrical energy storage means comprises apparatus for charging at least one capacitor during a powered locking stroke of the actuator, and during a subsequent powered stall of the actuator.
- 15. The system defined in claim 12, wherein the apparatus for storing energy in the electrical energy storage means comprises apparatus for charging a rechargeable battery during a powered locking stroke of the actuator, and during a subsequent powered stall of the actuator.
- 16. The system defined in claim 12, wherein the apparatus for storing energy in the mechanical energy storage means and the electrical energy storage means are fully redundant.
- 17. The system defined in claim 12, wherein the apparatus for controlling the linear velocity of the actuator comprises apparatus for:
sensing a rotational speed of an actuator motor; sensing a first current supplied to the motor; reducing the first current if the rotational speed is higher than a maximum speed, or if the first current is higher than a maximum current.
- 18. The system defined in claim 17, wherein the apparatus for controlling the linear velocity of the actuator further comprises apparatus for:
shunting a second current generated by the motor into a damper circuit to place an electrical load on the motor if the first current is substantially zero and the rotational speed is higher than the maximum speed.
- 19. The system defined in claim 17, wherein the apparatus for sensing the rotational speed of the motor comprises apparatus for measuring a frequency of a Hall effect sensor signal.
- 20. The system defined in claim 17, wherein the apparatus for sensing the rotational speed of the motor comprises apparatus for measuring a back electro-motive force generated by the motor.
- 21. The system defined in claim 17, wherein the apparatus for reducing the first current comprises apparatus for reducing a voltage supplied to the motor.
- 22. The system defined in claim 17, wherein the apparatus for reducing the first current comprises apparatus for pulse-width-modulating a power signal supplied to the motor.
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application is a divisional of U.S. patent application Ser. No. 10/260,470, filed Sep. 26, 2002, which claims priority from U.S. provisional application No. 60/348,881, filed Nov. 13, 2001, both of which are hereby incorporated by reference herein in their entireties.
Provisional Applications (1)
|
Number |
Date |
Country |
|
60348881 |
Nov 2001 |
US |
Divisions (1)
|
Number |
Date |
Country |
Parent |
10260470 |
Sep 2002 |
US |
Child |
10658930 |
Sep 2003 |
US |