Skin Impact Snubber

Patent metadata

Field	Value
Publication number	US-2016185436-A1
Application number	US-201414293250-A
Country	US
Kind code	A1
Filing date	Jun 2, 2014
Priority date	Mar 6, 2014
Publication date	Jun 30, 2016
Grant date	—

Abstract

In some embodiments, an aircraft includes a structural assembly, a skin, and a snubber. The structural assembly comprises a first rigid element and a second rigid element. The first and second rigid elements are separated from each over by a void. The skin is disposed proximate to the structural assembly and adjacent to the void such that the skin would deflect into the void in response to an impact force received by the skin. The snubber is disposed in the void between the first and second rigid elements and positioned such that, when the skin deflects in response to the impact force, the skin contacts the snubber and the snubber reduces further deflection of the skin into the void.

First claim

What is claimed is:

1 . An aircraft comprising:
a structural assembly comprising a first rigid element and a second rigid element, the first and second rigid elements separated from each over by a void; a skin disposed proximate to the structural assembly and adjacent to the void such that the skin would deflect into the void in response to an impact force received by the skin; and a snubber disposed in the void between the first and second rigid elements and positioned such that, when the skin deflects in response to the impact force, the skin contacts the snubber and the snubber reduces further deflection of the skin into the void.

2 . The aircraft of claim 1 , wherein:
the skin would deflect into the void along a deflection path in response to the impact force received by the skin; and the snubber is positioned such that, when the skin deflects in response to the impact force, the skin contacts the snubber at a point along the deflection path and the snubber reduces further deflection of the skin into the void.

3 . The aircraft of claim 2 , wherein the skin contacts the snubber at the point along the deflection path such that, if the snubber was not disposed in the void, the skin would deflect along the deflection path unencumbered past the point in response to the impact force.

4 . The aircraft of claim 1 , wherein the first rigid element comprises a spar configured to provide rigid support to an aircraft fuselage.

5 . The aircraft of claim 1 , wherein the second rigid element comprises a protective housing disposed within an aircraft fuselage.

6 . The aircraft of claim 1 , wherein the skin is in contact with the first and second rigid elements.

7 . The aircraft of claim 1 , wherein the skin and the snubber are situated such that they are not in contact other than when the skin deflects in response to the impact force.

8 . The aircraft of claim 1 , wherein the snubber is coupled to the first rigid element and the second rigid element.

9 . The aircraft of claim 8 , wherein the snubber is removably coupled to the first rigid element and the second rigid element.

10 . The aircraft of claim 1 , wherein the aircraft is a rotorcraft comprising:
a body, the body comprising the structural assembly, the skin, and the snubber; a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine; and a rotor system coupled to the power train, the rotor system comprising at least one rotor blade.

11 . A method of reducing damage to a skin of an aircraft caused by an impact force, the aircraft comprising a structural assembly comprising a first rigid element and a second rigid element, the first and second rigid elements separated from each over by a void, the skin being disposed proximate to the structural assembly and adjacent to the void such that the skin would deflect into the void in response to an impact force received by the skin, the method comprising:
receiving, by the skin, the impact force; and providing a snubber in the void between the first and second rigid elements and such that, when the skin deflects in response to the impact force, the skin contacts the snubber and the snubber reduces further deflection of the skin into the void.

12 . The method of claim 11 , wherein:
the skin would deflect into the void along a deflection path in response to the impact force received by the skin; and providing the snubber in the void between the first and second rigid element comprises providing the snubber such that, when the skin deflects in response to the impact force, the skin contacts the snubber at a point along the deflection path and the snubber reduces further deflection of the skin into the void.

13 . The method of claim 12 , wherein the skin contacts the snubber at the point along the deflection path such that, if the snubber was not disposed in the void, the skin would deflect along the deflection path unencumbered past the point in response to the impact force.

14 . The method of claim 11 , wherein the first rigid element comprises a spar configured to provide rigid support to an aircraft fuselage.

15 . The method of claim 11 , wherein the second rigid element comprises a protective housing disposed within an aircraft fuselage.

16 . The method of claim 11 , wherein the skin is in contact with the first and second rigid elements.

17 . The method of claim 11 , wherein the skin and the snubber are situated such that they are not in contact other than when the skin deflects in response to the impact force.

18 . The method of claim 11 , wherein the snubber is coupled to the first rigid element and the second rigid element.

19 . The method of claim 18 , wherein the snubber is removably coupled to the first rigid element and the second rigid element.

20 . The method of claim 1 , wherein the aircraft is a rotorcraft comprising:
a body, the body comprising the structural assembly, the skin, and the snubber; a power train coupled to the body and comprising an engine and a drive shaft coupled to the engine; and a rotor system coupled to the power train, the rotor system comprising at least one rotor blade.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Wittmaak Jr John R
• Hannan Philip J
• Lucas Maxx S
• Tiwari Chandrashekhar

Classifications

• B64C1/06 Primary

  Frames; Stringers; Longerons {; Fuselage sections} · CPC title

• B64C27/04

  Helicopters · CPC title

• B64D2045/0095

  Devices specially adapted to avoid bird strike · CPC title

• B64C27/006

  Safety devices · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title