Aircraft wing slat skew detection systems and methods

Patent metadata

Field	Value
Publication number	US-9815570-B2
Application number	US-201514683036-A
Country	US
Kind code	B2
Filing date	Apr 9, 2015
Priority date	Apr 9, 2015
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

An apparatus for detecting skew in a slat of an aircraft wing includes an elongated track moveably supported in the wing for longitudinal movement toward and away from a leading edge of the wing. The slat is coupled to a forward end of the track for conjoint movement therewith. An actuator is configured to selectably drive the track and slat between retracted and extended positions relative to the leading edge of the wing. A pinion gear is rotatably mounted in the wing and disposed in rolling engagement with a rack gear disposed on the track, and a sensor is coupled to the pinion gear and configured to sense the longitudinal position of the slat as a function of a rotational position of the pinion gear.

First claim

What is claimed is:

1. An apparatus, comprising:
an elongated track moveably supported in a wing of an aircraft for longitudinal movement toward and away from a leading edge of the wing, the track having a forward end coupled to a wing slat for conjoint movement therewith;
a rack gear disposed on the track;
a drive gear mounted on a first shaft for rotation within the wing and disposed in meshing engagement with the rack gear of the track;
an actuator drivingly coupled to the first shaft and operable to selectably rotate the drive gear in opposite directions so as to selectably drive the track between retracted and extended positions relative to the leading edge of the wing;
a pinion gear mounted on a second shaft for rotation within the wing and disposed in rolling engagement with the rack gear on the track, the second shaft being distinct from the first shaft; and
a sensor coupled to the pinion gear and configured to sense a longitudinal position of the slat as a function of a rotational position of the pinion gear.

2. The apparatus of claim 1 , wherein the track is supported in the wing by a pair of support ribs located within the wing and respectively disposed on opposite sides of the track.

3. The apparatus of claim 1 , wherein the track is moveably supported in the wing by at least one roller bearing or at least one ball bearing.

4. The apparatus of claim 1 , wherein the pinion gear is disposed on a shaft that is rotatably mounted in the wing by at least one roller bearing or at least one ball bearing.

5. The apparatus of claim 1 , wherein the sensor is rotatably coupled to the pinion gear through a gear train.

6. The apparatus of claim 1 , wherein the pinion gear comprises a sector gear.

7. The apparatus of claim 1 , wherein the sensor comprises an encoder, a potentiometer, or a resolver.

8. The apparatus of claim 1 , wherein the sensor comprises a shaft encoder, and wherein the shaft encoder comprises a conductive encoder, an optical encoder, an on-axis magnetic encoder or an off-axis magnetic encoder.

9. An aircraft comprising the apparatus of claim 1 , wherein the apparatus is within the wing of the aircraft.

10. A method, comprising:
coupling the forward end of the track of the apparatus of claim 1 to an end of the slat; and
sensing the longitudinal position of the end of the slat relative to the leading edge of the wing using the sensor.

11. The method of claim 10 , further comprising detecting a skewed condition of the slat using the sensed position of the end of the slat.

12. The method of claim 11 , wherein the detecting comprises comparing the sensed position of the end of the slat with a position of an opposite end of the slat.

13. The method of claim 11 , wherein the detecting comprises comparing the sensed position of the end of the slat with a position of an end of another slat.

14. A method, comprising:
driving an end of a wing slat longitudinally with an elongated track between a retracted position and an extended position relative to a leading edge of the wing using an actuator coupled to the elongated track through a first shaft and a drive gear;
rotating a rotary position sensor using the elongated track coupled to the sensor through a pinion gear and a second shaft, the second shaft being distinct from the first shaft; and
sensing a longitudinal position of the end of the slat as a function of a rotational position of the pinion gear.

15. The method of claim 14 , further comprising detecting a skewed condition of the slat using the sensed position of the end of the slat.

16. The method of claim 15 , wherein the detecting comprises comparing the sensed position of the end of the slat with a position of an opposite end of the slat or a position of an end of another slat.

Assignees

• Boeing Co

Inventors

• Anderson Randall Eugene

Classifications

• B64D45/0005 Primary

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• F16H19/04

  comprising a rack · CPC title

• B64D2045/001

  for indicating symmetry of flaps deflection · CPC title