REDUNDANT TWO STAGE ELECTRO-HYDRAULIC SERVO ACTUATOR CONTROL

• US 20120253556A1
• Filed: 03/31/2011
• Published: 10/04/2012
• Est. Priority Date: 03/31/2011
• 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: Noll, Christopher, Avritch, Steven A.
• Granted Patent: US 8,534,599 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 13/503 Fly-by-Wire
• CPC Class Codes: B64C 13/504 using electro-hydrostatic actuators [EHA's]
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions

Abstract

A flight control system includes a dual stage actuator for moving a control surface. Each stage includes several control valves that are controlled independently to provide a desired redundancy. A flight controller generates a position command that is indicative of the position desired for the control surface. A first communication link is provided between several flight controllers to share information. Each of the flight controllers forwards the position command to actuator remote processing unit. The actuator remote processing unit receives position commands and generates a command signal that controls movement of the actuator using the control valves. Each of the actuator remote processing units is linked through a second communication link. Feedback and balancing of the different control valves is provided by the visibility accorded each actuator remote processing unit by the second communication link.

Claims

1. A flight control system comprising:

a first flight controller and a second flight controller generating position commands indicative of a desired position of an actuator required to move a flight control surface to a desired position;

a first data link between the first flight controller and the second flight controller communicating information between the first and second flight controllers;

a first actuator remote processing unit and a second actuator remote processing unit receiving position commands from a corresponding one of the first flight controller and the second flight controller, the first and second actuator remote processing units generating commands for the actuator based on the received position commands;

a first sensor and a second sensor communicating information indicative of actuator operation to a corresponding one of the first and second actuator remote processing units; and

a second data link between the first and second actuator remote processing units communicating data received from the first and second sensors to each of the first and second actuator remote processing units independent of the first and second flight controllers, wherein the first and second actuator remote processing units generate the commands for the actuator based further on the data received from the other of the actuator remote processing units.

2. The flight control system as recited in claim 1, wherein the first and second actuator remote processing units further generate the commands based on data shared over the second data link.

3. The flight control system as recited in claim 1, wherein the actuator includes a first stage and a second stage and each of the first and second actuator remote processing units comprise a pair of actuator remote processing units for controlling one of the first and second stages.

4. The flight control system as recited in claim 3, wherein the actuator includes a plurality of first stage control valves and a plurality of second stage control valves, each pair of the actuator remote processing units control one of the first stage control valves and one of the second stage control valves.

5. The flight control system as recited in claim 4, including a third flight controller generating position commands indicative of a desired position of the actuator and a third actuator remote processing unit comprising a pair of actuator remote processing units generating commands based on the received position commands from the third flight controller, wherein the third actuator remote processing unit communicates information with the first and second actuator remote processing units through the second data link.

6. The flight control system as recited in claim 1, including a position sensor generating a position command indicative of a position of the actuator, wherein the position command is communicated through the first and second actuator remote processing units to the first and second controllers and between the first and second actuator remote processing units through at least the second data link.

7. The flight control system as recited in claim 1, wherein the actuator comprises a dual stage electro-hydraulic actuator.

8. The flight control system as recited in claim 7, wherein each of the first and second sensors comprises a pressure sensor communicating a value indicative of hydraulic pressure to the corresponding actuator remote processing unit.

9. The flight control system as recited in claim 1, including communicating a condition of the actuator between the first and second actuator remote processing units over the second data link and comparing the communicated condition reported by each of the first and second actuator remote processing units to detect an aberrant condition.

10. The flight control system as recited in claim 9, including comparing data obtained from the first and second sensors between the first and second actuator remote processing units for detecting an aberrant reading from one of the first and second sensors.

11. A method of controlling a control surface of an aircraft comprising:

generating separate position commands indicative of a desired position of a common control surface with at least two independently operable flight controllers;

communicating information by way of a first data link between the at least two independently operable flight controllers;

receiving the position command from each of the flight controller with a corresponding actuator remote processing unit and generating a command signal for an actuator;

receiving feedback information indicative of actuator operation with the actuator remote processing unit;

communicating feedback information indicative of actuator operation through a second data link between each of the actuator remote processing units; and

modifying the command signals for the actuator generated by the actuator remote processing unit responsive to information obtained through the second data link.

12. The method as recited in claim 11, including the step of controlling one of a plurality of control valves with each actuator remote processing unit and receiving information indicative of pressure and control valve position with each actuator remote processing unit through the second data link.

13. The method as recited in claim 12, including comparing information indicative of operation of each control valve and determining that one of the plurality of control valves is not operating as desired responsive to information indicative of operation for one of the plurality of control valves differing from the other controls valves beyond a desired tolerance range.

14. The method as recited in claim 11, including sensing a position of the actuator utilizing a position sensor and communicating the position of the sensor back to each of the actuator remote processing units through a feedback loop and across the second data link.

15. The method as recited in claim 11, wherein the actuator comprises a first stage and a second stage and each of the actuator remote processing units comprises a pair of actuator remote processing units each generating command signals for a control valve associated with one of the first stage and the second stage.