Aircraft assembly including deflection sensor

• US 10,654,564 B2
• Filed: 12/06/2017
• Issued: 05/19/2020
• Est. Priority Date: 12/15/2016
• Status: Active Grant

• Current Assignee: Safran Landing Systems UK Limited, Messier-Dowty Limited (Safran SA)
• Original Assignee: Safran Landing Systems UK Limited
• Inventors: Cokonaj, Valerijan, Collett, Laura
• Primary Examiner(s): Nguyen, Bao Long T
• Assistant Examiner(s): Berns, Michael A
• Application Number:
  US15/833,549
• Publication Number:
  US 20180170531A1
• Time in Patent Office: 895 Days
• CPC Class Codes: B64C 25/02 Undercarriages
• CPC Class Codes: B64C 25/58 Arrangements or adaptations of shock-absorbers or springs shimmy-dampers B64C25/50
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: G01C 19/5776 Signal processing not specific to any of the devices covered by groups G01C19/5607 - G01C19/5719

Abstract

An aircraft assembly having a first region, a second region spaced from the first region by a flexible region, and a deflection sensor. The first region has greater positional stability than the second region such that the second region deflects further from its default position than the first region during in-use loads. The deflection sensor includes a first gyroscope at the first region to generate a first signal representing rotation of the first region about one or more orthogonal axes, and a second gyroscope at the second region to generate a second signal representing rotation of the second region about the one or more axes. The second gyroscope is synchronised in time with the first. A controller subtracts one of the first and second signals from the other to obtain a differential signal representing deflection of the second region relative to the first due to flexing of the flexible region.

Claims

1. An aircraft landing gear assembly comprising:

a shock-absorbing strut comprising a cylinder and a sliding tube;

attachment lugs configured to couple the shock-absorbing strut to an aircraft airframe;

a first region at or adjacent to the attachment lugs;

a second region spaced from the first region by a flexible region, the flexible region comprising at least a portion of the shock-absorbing strut, the first region having greater positional stability than the second region such that flexing of the flexible region due to in-use loads causes the second region to deflect further from a second default position than the first region deflects from a first default position; and

a deflection sensor comprising;

a first gyroscope rigidly mounted at, or with respect to, the first region so as to generate a first signal which represents rotation of the first region about one or more orthogonal axes;

a second gyroscope rigidly mounted at, or with respect to, the second region so as to generate a second signal which represents rotation of the second region about the one or more orthogonal axes, the second gyroscope being synchronised in time with the first gyroscope; and

a controller communicatively coupled to the first and second gyroscopes to receive the first and second signals, the controller being configured to subtract one of the first and second signals from the other to obtain a differential signal which represents deflection of the second region relative to the first region due to flexing of the flexible region.

2. The aircraft assembly according to claim 1, wherein the first region is at or adjacent to an attachment formation via which a component of the assembly is arranged to be coupled to another component of the assembly.

3. The aircraft assembly according to claim 2, wherein the flexible region is an aircraft landing gear main strut, the first region is at or adjacent to coupling lugs via which the strut is arranged to be pivotally coupled to an airframe and the second region is relatively closer to a distal end of the strut with respect to the coupling lugs to measure deflection of the strut.

4. The aircraft assembly according to claim 3, wherein strut is a main shock absorbing strut comprising an outer cylinder, which defines the coupling lugs, slidably coupled to an inner sliding tube, on which the second region is located, and wherein the deflection sensor further comprises a shock absorber extension sensor arranged to measure an extension state of the main shock absorbing strut.

5. The aircraft assembly according to claim 2, wherein the flexible region is an aircraft landing gear main strut, the first region is at or adjacent to an airframe which defines a landing gear bay and the second region is relatively closer to a distal end of the strut with respect to the airframe which defines the landing gear bay.

6. The aircraft assembly according to claim 1, wherein the deflection sensor comprises one or more further gyroscopes each rigidly mounted at, or with respect to, further regions so as to each generate a further signal which represents rotation of the further region about the one or more orthogonal axes, wherein each further region is spaced from the first or second region or a different further region by a further flexible region, the first or second region or different further region having greater positional stability than the further region such that flexing of the further flexible region due to in-use loads causes the further region to deflect further from its default position than the first or second region or different further region deflects from its default position and wherein the controller is communicatively coupled to each of further gyroscopes to receive the further signals and process them in the same manner to obtain a differential signal which represents deflection of the further flexible region.

7. The aircraft assembly according to claim 1, wherein the gyroscopes are each rigidly mounted at or adjacent to the respective regions by rigid brackets.

8. The aircraft assembly according to claim 1, wherein one or more or each gyroscope is an array of gyroscopes arranged to measure rotation in three orthogonal axes.

9. The aircraft assembly according to claim 1, wherein the first gyroscope and the second gyroscope are of equal construction.

10. The aircraft assembly according to claim 1, wherein one or more or each gyroscope forms part of an inertial measurement unit (IMU) including one or more accelerometers arranged to measure accelerations in the one or more orthogonal axes.

11. The aircraft assembly according to claim 10, wherein the one or more accelerometers are arranged to measure accelerations in three orthogonal axes.

12. The aircraft assembly according to claim 1, wherein the controller comprises a plurality of distributed controllers communicatively coupled to one another.

13. A computer implemented method of measuring deflection of an aircraft assembly according to claim 1, comprising a first region and a second region spaced from the first region by a flexible region, the first region having greater positional stability than the second region such that flexing of the flexible region due to in-use loads causes the second region to deflect further from a second default position than the first region deflects from a first default position, the method comprising:

receiving at a controller a first signal from a first gyroscope rigidly mounted at, or with respect to, the first region, the first signal representing rotation of the first region about one or more orthogonal axes;

receiving at the controller a second signal from a second gyroscope rigidly mounted at, or with respect to, the second region, the second signal representing rotation of the second region about one or more orthogonal axes, the second gyroscope being synchronised in time with the first gyroscope; and

subtracting one of the first and second signals from the other to obtain a differential signal which represents level of deflection of second region relative to the first region due to flexing of the flexible region.

14. An aircraft landing gear assembly comprising:

a shock-absorbing strut comprising a cylinder and a sliding tube;

an axle transverse to the shock-absorbing strut;

a first region;

a second region spaced from the first region by a flexible region, the first region having greater positional stability than the second region such that flexing of the flexible region due to in-use loads causes the second region to deflect further from a second default position than the first region deflects from a first default position; and

a deflection sensor comprising;

a first gyroscope rigidly mounted at, or with respect to, the first region so as to generate a first signal which represents rotation of the first region about one or more orthogonal axes;

a second gyroscope rigidly mounted at, or with respect to, the second region so as to generate a second signal which represents rotation of the second region about the one or more orthogonal axes, the second gyroscope being synchronised in time with the first gyroscope; and

a controller communicatively coupled to the first and second gyroscopes to receive the first and second signals, the controller being configured to subtract one of the first and second signals from the other to obtain a differential signal which represents deflection of second region relative to the first region due to flexing of the flexible region;

wherein the flexible region comprises the axle and, the second region is relatively closer to a free end of the axle than the first region is, and the deflection sensor is arranged to measure deflection of the axle.

15. An aircraft landing gear assembly comprising:

a shock-absorbing strut comprising a cylinder and a sliding tube;

an axle transverse to the shock-absorbing strut;

a first region;

a second region spaced from the first region by a flexible region, the first region having greater positional stability than the second region such that flexing of the flexible region due to in-use loads causes the second region to deflect further from a second default position than the first region deflects from a first default position; and

a deflection sensor comprising;

a first gyroscope rigidly mounted at, or with respect to, the first region so as to generate a first signal which represents rotation of the first region about one or more orthogonal axes;

a second gyroscope rigidly mounted at, or with respect to, the second region so as to generate a second signal which represents rotation of the second region about the one or more orthogonal axes, the second gyroscope being synchronised in time with the first gyroscope; and

a controller communicatively coupled to the first and second gyroscopes to receive the first and second signals, the controller being configured to subtract one of the first and second signals from the other to obtain a differential signal which represents deflection of the second region relative to the first region due to flexing of the flexible region;

wherein the first or second region is at or adjacent the middle of the axle, and the flexible region comprises at least a portion of the shock-absorbing strut or at least a portion of the axle.