Low load shear out auxiliary support joint

Patent metadata

Field	Value
Publication number	US-11447233-B2
Application number	US-201916550675-A
Country	US
Kind code	B2
Filing date	Aug 26, 2019
Priority date	Aug 26, 2019
Publication date	Sep 20, 2022
Grant date	Sep 20, 2022

Abstract

A flap support structure incorporates an auxiliary flap support attachment fitting and an auxiliary flap support track. A primary load pin couples the auxiliary support track to the auxiliary flap support attachment fitting and reacts operating loads on the flap. At least one fuse pin extends through the primary load pin to limit translation of the primary load pin relative to the attachment fitting.

First claim

What is claimed is:

1. A flap support structure comprising:
a flap support attachment fitting;
a flap support track;
a primary load pin coupling the flap support track to the flap support attachment fitting, said primary load pin transverse to the flap support attachment fitting reacting operating loads; and
at least one fuse pin extending through the primary load pin to limit translation of the primary load pin relative to the attachment fitting, the flap support attachment fitting configured for translation of the primary load pin aligned with flap deployment loads upon fracture of the at least one fuse pin.

2. The flap support structure as defined in claim 1 wherein the primary load pin is engaged in inboard and outboard slots in the flap support attachment fitting.

3. The flap support structure as defined in claim 2 wherein the at least one fuse pin is configured to fracture when subject to a shear out load, said primary load pin translating in the inboard and outboard slots upon shearing of the at least one fuse pin.

4. The flap support structure as defined in claim 3 further comprising a spherical bearing mounted in the flap support track wherein the primary load pin is received through the spherical bearing and has end portions received in the inboard and outboard slots.

5. The flap support structure as defined in claim 4 wherein the end portions of the primary load pin have opposing flats received on upper and lower surfaces of the inboard and outboard slots.

6. The flap support structure as defined in claim 4 wherein the flap support attachment fitting further comprises a central channel between an inboard fitting extension and an outboard fitting extension, the central channel receiving an aft lug of the flap support track, the spherical bearing mounted in the aft lug.

7. The flap support structure as defined in claim 6 wherein the at least one fuse pin comprises two transverse fuse pins received through pin receiving bores in the inboard and outboard fitting extensions and mating bores in the end portions, wherein in an operating condition in which the flap support track is not jammed, the mating bores are concentrically aligned with the pin receiving bores.

8. The flap support structure as defined in claim 7 wherein the inboard and outboard slots are aligned with flap deployment loads induced by the flap support track on the flap support attachment fitting and the transverse fuse pins are aligned transverse to the inboard and outboard slots to react shear forces along the inboard and outboard slots.

9. The flap support structure as defined in claim 7 wherein the transverse fuse pins are incorporated in fuse pin assemblies having
heads at a first end of the transverse fuse pins constraining the transverse fuse pins at an interface of the receiving bores; and,
nuts received in lateral bores in the inboard and outboard fitting extensions to align with the pin receiving bores allowing threaded engagement of the transverse fuse pins to constrain the transverse fuse pins in the flap support attachment fitting.

10. The flap support structure as defined in claim 6 wherein the at least one fuse pin comprises an axial fuse pin received through lateral pin bores in the inboard and outboard fitting extensions and extending through an axial bore in the primary load pin, wherein in an operating condition in which the flap support track is not jammed, the lateral pin bores are concentrically aligned with the axial bore.

11. The flap support structure as defined in claim 3 further comprising a ramp on the flap support track, the ramp engaging the flap support attachment fitting in a jam condition upon translation of the primary load pin out of an aft end of the inboard and outboard slots.

12. An operating flap system for an aircraft, said system comprising:
a flap supported by at least one primary support with an actuator driven mechanism and a passively operating auxiliary support providing deflection control and carrying loads from the flap;
an auxiliary flap support track operatively engaged by the auxiliary support and configured to extend upon deployment of the flap and retract upon retraction of the flap;
an auxiliary flap support attachment fitting;
a primary load pin coupling the auxiliary support track to the auxiliary flap support attachment fitting, said primary load pin transverse to the auxiliary flap support attachment fitting reacting operating loads on the flap; and
at least one fuse pin extending through the primary load pin to limit translation of the primary load pin relative to the attachment fitting, said at least one fuse pin reacting shear loads induced on the primary load pin by the auxiliary flap support track, the auxiliary flap support attachment fitting configured for translation of the primary load pin aligned with flap deployment loads upon fracture of the at least one fuse pin.

13. The operating flap system as defined in claim 12 wherein the primary load pin is engaged in inboard and outboard slots in the auxiliary flap support attachment fitting, and further comprising a spherical bearing mounted in the auxiliary flap support track wherein the primary load pin is received through the spherical bearing and has end portions received in the inboard and outboard slots, the end portions having opposing flats received on upper and lower surfaces of the inboard and outboard slots, and wherein the at least one fuse pin is configured to fracture when subject to a shear out load, said primary load pin translating in the inboard and outboard slots upon shearing of the at least one fuse pin.

14. The operating flap system as defined in claim 13 wherein the auxiliary flap support attachment fitting further comprises a central channel between an inboard fitting extension and an outboard fitting extension, the central channel receiving an aft lug of the auxiliary flap support track, the spherical bearing mounted in the aft lug.

15. The operating flap system as defined in claim 13 wherein the at least one fuse pin comprises two transverse fuse pins received through pin receiving bores in the inboard and outboard fitting extensions and mating bores in the end portions, wherein in an operating condition in which the auxiliary flap support track is not jammed, the mating bores are concentrically aligned with the pin receiving bores and the fuse pins are incorporated in fuse pin assemblies having
heads at a first end of the transverse fuse pins constraining the transverse fuse pins at an interface of the pin receiving bores; and,
nuts received in lateral bores in the inboard and outboard fitting extensions to align with the pin receiving bores allowing threaded engagement of the transverse fuse pins to constrain the transverse fuse pins in the auxiliary flap support attachment fitting, wherein the inboard and outboard slots are aligned with flap operating loads induced by the auxiliary flap support track on the auxiliary flap support attachment fitting and the transverse fuse pins are aligned transverse to the inboard and outboard slots to react shear forces along the inboard and outboard slots, said transverse fuse pins configured to fracture responsive to a shear out load to allow translation of the primary load pin in the inboard and outboard slots.

16. The operating flap system as defined in claim 14 further comprising a ramp on the auxiliary flap support track, the ramp engaging the auxiliary flap support attachment fitting in a jam condition upon translation of the primary load pin out of an aft end of the inboard and outboard slots.

17. A method for

Assignees

• Boeing Co

Inventors

• Gruner Bryan J
• Homrich John Thomas B

Classifications

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C9/18

  by single flaps · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• Y02T50/40

  Weight reduction · CPC title