Detection of effort on a flight-control actuator

• US 7,946,529 B2
• Filed: 03/21/2008
• Issued: 05/24/2011
• Est. Priority Date: 03/23/2007
• Status: Active Grant

• Current Assignee: Goodrich Actuation System SAS (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Actuation System SAS (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Sellier, Philippe, Moalic, Jean-Marc, Turpin, Pierre
• Primary Examiner(s): Ellis; Christopher P
• Application Number:
  US12/053,258
• Publication Number:
  US 20080315040A1
• Time in Patent Office: 1,159 Days
• Field of Search: 244/99.4, 244/99.3, 244/99.2
• US Class Current: 244/99.4
• CPC Class Codes: B64C 13/341 having duplication or stand-by provisions
• CPC Class Codes: F16H 2025/2037 Actuator supports or means for fixing piston end, e.g. flanges
• CPC Class Codes: F16H 25/2021 with means for avoiding overloading
• CPC Class Codes: F16H 25/205 comprising alternate power paths, e.g. for fail safe back-up

Abstract

The use of at least one attachment screw (12) that includes means (14, 15, 17a, 17b, 20) for detecting the secondary path loading of a flight-control actuator, or associated with a bush that includes such means, for the attachment of the top coupling of the secondary path of a flight-control actuator.

Claims

1. A flight-control actuator having a primary path and a secondary path adapted to take up effort of the primary path in the event of failure thereof, the primary path including a screw, the screw terminating in a coupling part of the primary path, the secondary path including a fail-safe effort take-up bar traversing the screw, the bar terminating in a male shape having a functional gap when the primary path is carrying the effort, the male shape placed in a female shape of a coupling part of the secondary path, the male shape terminating the bar and the female shape of the coupling part being spherical or rotational, top coupling of the secondary path being provided by the female shape of the coupling part, an attachment yoke of an aircraft, and a nut and bolt attachment means, the actuator including means for detecting loading of the secondary path,

characterised in that said detection means of secondary path loading including at least one sensor adapted to detect an effort (14, 15, 17a, 17b, 20) applied to at least one of the parts (8, 11, 12) performing the top coupling of the secondary path, and adapted to detect stressing of the latter.

2. An actuator according to claim 1, characterised in that the sensor adapted to detect an effort is located on at least one attachment screw (12) performing the top coupling of the secondary path and/or on a bush (19) attached to the latter.

3. An actuator according to claim 1, characterised in that the sensor adapted to detect an effort includes one or more strain gauges (14, 15).

4. An actuator according to claim 2 wherein the sensor adapted to detect an effort includes one or more strain gauges, characterised in that it includes at least one strain-gauge blade (14, 15) located on an indentation presented by an attachment screw opposite to a hole of a yoke of the coupling part (8) of the secondary path in which it is accommodated, the yoke having a projecting element (16) at the hole which is adapted to load the blade at least in certain loading configurations.

5. An actuator according to claim 4, characterised in that it includes at least three strain-gauge blades (14, 15) distributed regularly around a periphery of the screw.

6. An actuator according to claim 1, characterised in that the sensor adapted to detect an effort, includes means (17a) to excite into vibration the attachment screw (12) of the top coupling of the secondary path, and/or a bush attached to the latter, and means (17b) to sense the vibration thus generated on the excited part, and processing means for detecting a change in the frequency response of the excited parts.

7. An actuator according to claim 6, characterised in that the means of excitation (17a) and the means (17b) to sense the vibration are of the piezoelectric type.

8. An actuator according to claim 1, characterised in that at least the yoke of the coupling part (8) of the secondary path includes a deformable bush (19), and has at least one pressure sensor (20).

9. An actuator according to claim 8, characterised in that the deformable bush (19) includes an envelope filled with silicon oil and a silicon bridge pressure sensor (20).

10. An actuator according to claim 1, characterised in that it includes several detection means (17a, 17b) located on one or more of the parts performing the attachment of the top coupling of the secondary path, the several detection means providing a redundancy of measurements or additional measurements.

11. An actuator according to claim 1, characterised in that at least one attachment screw (12) that includes means forming a sensor adapted to detect an effort (14, 15, 17a, 17b, 20) or an assembly that includes an attachment screw and a bush that have such means, is used for actuator coupling attachment.

12. An actuator according to claim 1, characterised in that at least one attachment screw (12) that includes means forming a sensor adapted to detect an effort (14, 15, 17a, 17b, 20), or an assembly that includes an attachment screw and a bush that have such means, is used for the attachment of the top coupling of the secondary path of the actuator.

13. The use of the actuator according to claim 1, in which at least one attachment screw (12) includes means forming a sensor adapted to detect an effort (14, 15, 17a, 17b, 20) is substituted for an attachment screw of an actuator coupling part.