Method and apparatus for covering a fastener system

• US 10,051,767 B2
• Filed: 05/29/2015
• Issued: 08/14/2018
• Est. Priority Date: 09/28/2012
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Yoon, Ilsop Steven, Pate, Kevin Darrell, Pajel, Carissa Ann, Alberts, Todd Michael, Hansen, Darrin Michael
• Primary Examiner(s): ESTREMSKY, GARY WAYNE
• Application Number:
  US14/725,994
• Publication Number:
  US 20150271960A1
• Time in Patent Office: 1,173 Days
• Field of Search: 361218, 411337, 4113725, 4113726, 411373, 411377
• CPC Class Codes: B32B 2435/00 Closures, end caps, stoppers
• CPC Class Codes: B32B 37/0076 characterised in that the layers are not bonded on the totality of their surfaces
• CPC Class Codes: B32B 37/12 characterised by using adhesives
• CPC Class Codes: B32B 37/153 at least one layer is extruded and immediately laminated while in semi-molten state
• CPC Class Codes: B32B 37/18 involving the assembly of discrete sheets or panels only
• CPC Class Codes: B64D 45/02 Lightning protectors; Static dischargers in general H01T
• CPC Class Codes: F16B 11/006 by gluing gluing of plastics material B29C65/48
• CPC Class Codes: F16B 33/004 Sealing; Insulation by means of washers F16B43/001
• CPC Class Codes: F16B 37/14 Cap nuts; Nut caps or bolt caps
• CPC Class Codes: H05K 9/0067 Devices for protecting against damage from electrostatic discharge
• CPC Class Codes: H05K 9/0079 Electrostatic discharge protection, e.g. ESD treated surface for rapid dissipation of charges

Abstract

A method and apparatus for covering a fastener system. In one illustrative embodiment, an apparatus comprises a cover. The cover is configured to be placed over a fastener system at a surface of an object in which the fastener system is installed. The cover is comprised of a number of composite materials selected such that the cover is configured to reduce an effect of an electrical discharge, which occurs around the fastener system, on an environment outside the cover.

Claims

1. A process for covering a fastener system, the process comprising:

calculating a predetermined depth between a flange of a cover and a surface of an object;

placing a sealant material and the cover over a portion of the fastener system which extends above the surface of the object retaining the fastener system such that the cover comprises a monolithic domed form comprising a number of composite materials;

forming a contactless connection between the cover with the fastener system and the object so that the sealant material envelopes a radially extending flange of the cover and surrounds a portion of an outside surface of the cover, while maintaining a non-zero depth of the sealant material between a bottom of the flange and a surface of an object from which the fastener system extends; and

suppressing, using the sealant material and the cover, an effect of an electrical discharge, occurring around the fastener system, on an environment outside the cover.

2. The process of claim 1, further comprising, applying the sealant material over the fastener system at the surface of the object prior to placing the cover over the fastener system.

3. The process of claim 1, further comprising, applying the sealant material inside the cover prior to placing the cover over the fastener system.

4. The process of claim 1, wherein calculating the predetermined depth between the flange of the cover and the surface of the object is based on the fastener system and a requirement for a lightning strike test for the fastener system.

5. The process of claim 1, wherein the cover is filled with sealant material to a fill level so that when the cover is placed over the fastener system, sealant material is forced out of the cover to form a sealant layer at the predetermined depth and to form a fairing.

6. A process for reducing an effect of an electrical discharge, occurring at a fastener system, on an environment, the process comprising:

calculating a predetermined depth between a flange of a cover and a surface of an object;

selecting an amount of a sealant material and placing the sealant material inside a cover, the cover being a monolithic domed shaped composite;

encircling an exposed portion of the fastener system with the cover;

extruding, by placing the cover encircling the fastening system, the sealant material between a radially extending flange of the cover and an object retaining the fastener system; and

covering the radially extending flange with the sealant material, by fairing the sealant material extruded between the radially extending flange of the cover and the object retaining the fastener system, to form a fairing of sealant material from an exterior side of the cover to the object retaining the fastener system and forming a contactless connection between the cover with the fastener system and the object retaining the fastener system; and

suppressing an undesired release, in response to the electrical discharge, occurring at the fastener system, of a number of materials into the environment outside the cover;

wherein when the cover is placed over the fastener system, sealant material is forced out of the cover to form a sealant layer at the predetermined depth and to form the fairing; and

wherein the sealant material envelopes the radially extending flange of the cover and surrounds a portion of an outside surface of the cover, while maintaining a non-zero depth of the sealant material between a bottom of the flange and a surface of an object from which the fastener system extends.

7. The process of claim 6 further comprising, fabricating the cover as a pre-impregnated composite comprising a number of composite materials comprising at least one of:

a carbon fiber-reinforced plastic material, a fiber-reinforced polymer, a glass-reinforced plastic, an aramid fiber-reinforced material, a metallic material, a fiberglass material, a plastic material, a thermoplastic material, and a thermoset material.

8. The process of claim 6 further comprising:

fabricating the cover to comprise;

an electrical resistivity comprising a volume resistivity of about 1.0×

10⁹ ohm-meters (Ω

-m) or less when measured at about 40 volts (V), and an electrical resistivity comprising a surface resistivity of about 1.0×

10¹¹ ohm per square (Ω

/sq) or less when measured at about 100 volts (V) or less.

9. The process of claim 6, wherein calculating the predetermined depth between the flange of the cover and the surface of the object is based on the fastener system and a requirement for a lightning strike test for the fastener system.

10. A portion of an aircraft assembled according to a process for covering a fastener system, the process comprising:

calculating a predetermined depth between a flange of a cover and a surface of an object;

placing a sealant material and the cover over a portion of the fastener system which extends above the surface of the object retaining the fastener system such that the cover comprises a monolithic domed form comprising a number of composite materials;

forming a contactless connection between the cover with the fastener system and the object so that the sealant material envelopes a radially extending flange of the cover and surrounds a portion of an outside surface of the cover, while maintaining a non-zero depth of the sealant material between a bottom of the flange and a surface of an object from which the fastener system extends; and

suppressing, using the sealant material and the cover, an effect of an electrical discharge, occurring around the fastener system, on an environment outside the cover.

11. The portion of the aircraft assembled according to the process for covering the fastener system of claim 10, wherein the process further comprises:

applying the sealant material over the fastener system at the surface of the object prior to placing the cover over the fastener system.

12. The portion of the aircraft assembled according to the process for covering the fastener system of claim 10, wherein the process further comprises:

applying the sealant material inside the cover prior to placing the cover over the fastener system.

13. The portion of the aircraft assembled according to the process for covering the fastener system of claim 10, wherein calculating the predetermined depth between the flange of the cover and the surface of the object is based on the fastener system and a requirement for a lightning strike test for the fastener system.

14. The portion of the aircraft assembled according to the process for covering the fastener system of claim 10, wherein the cover is filled with sealant material to a fill level so that when the cover is placed over the fastener system, sealant material is forced out of the cover to form a sealant layer at the predetermined depth and to form a fairing.

15. A portion of a fuel tank assembled according to a process for reducing an effect of an electrical discharge, occurring at a fastener system, on an environment, the process comprising:

calculating a predetermined depth between a flange of a cover and a surface of an object;

selecting an amount of a sealant material and placing the sealant material inside a cover, the cover being a monolithic domed shaped composite;

encircling an exposed portion of the fastener system with the cover;

extruding, by placing the cover encircling the fastening system, the sealant material between a radially extending flange of the cover and an object retaining the fastener system; and

covering the radially extending flange with the sealant material, by fairing the sealant material extruded between the radially extending flange of the cover and the object retaining the fastener system, to form a fairing of sealant material from an exterior side of the cover to the object retaining the fastener system and forming a contactless connection between the cover with the fastener system and the object retaining the fastener system; and

suppressing an undesired release, in response to the electrical discharge, occurring at the fastener system, of a number of materials into the environment outside the cover;

wherein when the cover is placed over the fastener system, sealant material is forced out of the cover to form a sealant layer at the predetermined depth and to form the fairing; and

wherein the sealant material envelopes the radially extending flange of the cover and surrounds a portion of an outside surface of the cover, while maintaining a non-zero depth of the sealant material between a bottom of the flange and a surface of an object from which the fastener system extends.

16. The portion of the fuel tank assembled according to the process of claim 15, the process further comprising, fabricating the cover as a pre-impregnated composite comprising a number of composite materials comprising at least one of:

a carbon fiber-reinforced plastic material, a fiber-reinforced polymer, a glass-reinforced plastic, an aramid fiber-reinforced material, a metallic material, a fiberglass material, a plastic material, a thermoplastic material, and a thermoset material.

17. The portion of the fuel tank assembled according to the process of claim 15, the process further comprising:

fabricating the cover having an electrical resistivity comprising a volume resistivity of about 1.0×

10⁹ ohm-meters (Ω

-m) or less when measured at about 40 volts (V), and an electrical resistivity comprising a surface resistivity of about 1.0×

10¹¹ ohm per square (Ω

/sq) or less when measured at about 100 volts (V) or less.

18. The portion of the fuel tank assembled according to the process of claim 15, wherein calculating the predetermined depth between the flange of the cover and the surface of the object is based on the fastener system and a requirement for a lightning strike test for the fastener system.