Fly by wire servos with internal loop closure

Patent metadata

Field	Value
Publication number	US-9452824-B2
Application number	US-201514835950-A
Country	US
Kind code	B2
Filing date	Aug 26, 2015
Priority date	Feb 19, 2014
Publication date	Sep 27, 2016
Grant date	Sep 27, 2016

Abstract

Embodiments are directed to obtaining a first analog signal corresponding to a position error between a commanded gang output of a plurality of electro-mechanical actuators configured to be run in parallel with one another and a measured gang output of the plurality of electro-mechanical actuators, obtaining a second analog signal corresponding to an output torque, and processing, by a circuit, the first analog signal and the second analog signal to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.

First claim

What is claimed is:

1. A servo assembly comprising:
a hydraulic primary servo;
an actuator coupled to the primary servo and configured to drive the primary servo; and
at least one sensor configured to determine a difference between a desired ram position and an actual ram position driving a spool to perform a loop closure;
wherein the actuator comprises a plurality of electro-mechanical actuators coupled to the primary servo and configured to drive the primary servo.

2. The servo assembly of claim 1 , wherein the plurality of electro-mechanical actuators are configured to be run in parallel with one another.

3. The servo assembly of claim 1 , wherein the servo assembly is configured to communicate with at least one flight control computer of an aircraft via a communication bus.

4. The servo assembly of claim 1 , wherein the communication bus is configured to adhere to at least one of RS485, RS232, ARINC 629, and AFDX.

5. The servo assembly of claim 1 , wherein each of the electro-mechanical actuators is controlled via a separate fly by wire channel.

6. The servo assembly of claim 1 , further comprising:
a summation bar coupled to a plurality of output arms associated with the plurality of electro-mechanical actuators and configured to perform a mechanical averaging of differences in outputs of the electro-mechanical actuators.

7. The servo assembly of claim 6 , wherein a stiffness and damping are selected for the summation bar relative to the electro-mechanical actuators.

8. The servo assembly of claim 1 , wherein the at least one device comprises at least one sensor, and wherein the at least one sensor comprises at least one of: a rotary variable differential transformer and a linear variable differential transducer.

9. The servo assembly of claim 1 , wherein the servo assembly is configured to calculate a torque associated with the plurality of electro-mechanical actuators.

10. The servo assembly of claim 9 , further comprising:
a circuit configured to generate and output a discrete that indicates a status of the torque in terms of direction and magnitude.

11. A system comprising:
at least one flight control computer; and
at least one servo assembly coupled to the at least one flight control computer comprising:
a hydraulic primary servo;
an actuator coupled to the primary servo and configured to drive the primary servo; and
at least one sensor configured to determine a difference between a desired ram position and an actual ram position driving a spool to perform a loop closure;
wherein the actuator comprises a plurality of electro-mechanical actuators coupled to the primary servo and configured to drive the primary servo.

12. The system of claim 11 , wherein the at least one servo assembly is coupled to the at least one flight control computer via a serial communications bus, and wherein the at least one flight control computer is configured to issue commands to the at least one servo assembly via the serial communications bus, and wherein the at least one servo assembly is configured to provide feedback to the at least one flight control computer via the serial communications bus.

13. The system of claim 11 , wherein the plurality of electro-mechanical actuators are configured to be run in parallel with one another.

14. The system of claim 11 , wherein the at least one servo assembly comprises a summation bar coupled to a plurality of output arms associated with the plurality of electro-mechanical actuators and configured to perform a mechanical averaging of differences in outputs of the electro-mechanical actuators.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Cotton Bryan S
• Harrigan Matthew
• Winslow Christopher L

Classifications

• B64C13/40

  using fluid pressure · CPC title

• B64C2013/506

  Operations & Transport · mapped topic

• B64C27/68 Primary

  using electrical energy, e.g. having electrical power amplification · CPC title

• B64C13/503 Primary

  Fly-by-Wire · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic