Aircraft glazing attachment

Patent metadata

Field	Value
Publication number	US-9334041-B2
Application number	US-201213556477-A
Country	US
Kind code	B2
Filing date	Jul 24, 2012
Priority date	Jul 29, 2011
Publication date	May 10, 2016
Grant date	May 10, 2016

Abstract

A glazing unit is provided in which a two part bush is provided such that relative movement between a fastener, a glazing component and a wing skin is permitted, thus avoiding stress concentrations and lowering risk of damage in use.

First claim

The invention claimed is:

1. An aircraft glazing apparatus comprising:
an aircraft glazing component defining a bore,
a bush located within the bore, the bush comprising a first part engaged with the aircraft glazing component to move with the glazing component and a second part defining a fastener receiving formation,
in which, during use, the first part is movable together with the aircraft glazing component relative to the second part to permit relative movement between the aircraft glazing component and the fastener receiving formation.

2. The aircraft glazing apparatus according to claim 1 in which the second part is non-fixedly engaged in the first part.

3. The aircraft glazing apparatus according to claim 2 in which the second part is movable relative to the first part in a direction perpendicular to a main axis of the fastener receiving formation.

4. The aircraft glazing apparatus according to claim 3 in which the second part is movable relative to the first part in all directions perpendicular to the main axis of the fastener receiving formation.

5. The aircraft glazing apparatus according to claim 4 in which the first and second parts each define a bearing surface, which bearing surfaces are in sliding engagement and which lie generally perpendicular to the main axis of the fastener receiving formation.

6. The aircraft glazing apparatus according to claim 1 in which the first part defines an at least partially frustroconical outer surface engaged with a corresponding frustroconical surface of the bore of the aircraft glazing component.

7. The aircraft glazing apparatus according to claim 1 in which one of the first and second parts is constructed from a first material having a stiffness which is greater than the stiffness of a second material from which the other of the first and second parts is constructed.

8. The aircraft glazing apparatus according to claim 7 in which the first material is metallic, and the second material is an elastomer.

9. The aircraft glazing apparatus according to claim 7 in which the first part is constructed from the first material.

10. The aircraft glazing apparatus according to claim 1 in which the fastener receiving formation comprises a countersunk bore.

11. The aircraft glazing apparatus according to claim 1 in which the bush is constructed from an elastomer.

12. The aircraft glazing apparatus according to claim 1 , in which the second part protrudes through the first part and the second part is configured to locate against the aircraft component.

13. The aircraft glazing apparatus according to claim 1 , further comprising a fastener receivable in the fastener receiving formation, the fastener being configured to attach the aircraft glazing component to an aircraft component.

14. The aircraft glazing apparatus according to claim 1 in which the first part is configured to be spaced from the fastener.

15. An aircraft glazing attachment apparatus comprising:
a first bush part comprising a male frustroconical outer profile,
a second bush part defining a fastener receiving formation,
the fastener receiving formation being configured to receive a fastener which is attachable to an aircraft component,
in which the second bush part is configured to be movably mounted within the first bush part in use, and,
at least a portion of the first bush part is configured to be received between the second bush part and the aircraft glazing component.

16. The aircraft glazing attachment apparatus according to claim 15 in which the second part is movable relative to the first part in a direction perpendicular to a main axis of the fastener receiving formation.

17. The aircraft glazing attachment apparatus according to claim 16 in which the second part is movable relative to the first part in all directions perpendicular to the main axis of the fastener receiving formation.

18. The aircraft glazing attachment apparatus according to claim 17 in which the first and second parts each define a bearing surface, which bearing surfaces are in sliding engagement and which lie generally perpendicular to the main axis of the fastener receiving formation.

19. The aircraft glazing attachment apparatus according to claim 15 in which one of the first and second parts is constructed from a first material having a stiffness which is greater than the stiffness of a second material from which the other of the first and second parts is constructed.

20. The aircraft glazing attachment apparatus according to claim 19 in which the first material is metallic, and the second material is an elastomer.

21. An aircraft glazing attachment apparatus according to claim 19 in which the first part is constructed from the first material.

22. The aircraft glazing attachment apparatus according to claim 15 in which the first bush part is mechanically locked to an aircraft glazing component.

23. The aircraft glazing attachment apparatus according to claim 22 in which the first bush part defines a radial undercut to receive the aircraft glazing component.

24. An aircraft glazing apparatus, comprising:
an aircraft glazing component defining a bore,
a bush located within the bore, the bush comprising a first part engaged with the glazing component and a second part defining a fastener receiving formation,
in which, during use, the first part and the second part are relatively movable to permit relative movement between the aircraft glazing component and the fastener receiving formation, and
in which the first and second parts each define a bearing surface, which bearing surfaces are in sliding engagement and which lie generally perpendicular to the main axis of the fastener receiving formation,
a space being formed between the first and second parts on both sides of the sliding engagement in a direction of the main axis of the fastener receiving formation.

Assignees

• Edmond George
• Monteith John
• Case Robert
• Dawson Michael
• Airbus Operations Ltd

Inventors

• Edmond George
• Monteith John
• Case Robert
• Dawson Michael

Classifications

• B64C1/1492 Primary

  Structure and mounting of the transparent elements in the window or windscreen · CPC title

• F16B5/0241

  with the possibility for the connection to absorb deformation, e.g. thermal or vibrational · CPC title

• B64D47/06 Primary

  for indicating aircraft presence · CPC title

• B64C1/1476

  Canopies; Windscreens or similar transparent elements · CPC title

• F16B31/00

  Screwed connections specially modified in view of tensile load; Break-bolts (shape of thread {F16B33/02; in couplings F16D9/00}) · CPC title