Lightning protection in aircrafts constructed with carbon fiber reinforced plastic

Patent metadata

Field	Value
Publication number	US-10875663-B2
Application number	US-201715838008-A
Country	US
Kind code	B2
Filing date	Dec 11, 2017
Priority date	Dec 11, 2017
Publication date	Dec 29, 2020
Grant date	Dec 29, 2020

Abstract

The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

First claim

What is claimed is:

1. An apparatus comprising:
a first Carbon Fiber Reinforced Plastic (CFRP) panel;
a second CFRP panel that overlaps with the first CFRP panel in a vertical direction;
a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap; and
a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap,
wherein the pins include:
a first group of pins inside the first CFRP panel each having heads exposed at a bottom surface of the first CFRP panel; and
a second group of pins inside the second CFRP panel each having heads exposed at a top surface of the second CFRP panel.

2. The apparatus of claim 1 , wherein:
the first group of pins and the second group of pins have a corresponding spacing to electrically connect the first CFRP panel and the second CFRP panel when the first CFRP panel and the second CFRP panel overlap in the vertical direction and are joined by the fastener.

3. The apparatus of claim 2 , wherein:
the spacing of each of the first group of pins and the second group of pins is semi-random.

4. The apparatus of claim 1 , wherein:
the pins are parallel with the fastener and perpendicular to layers of carbon fiber in the first CFRP panel and the second CFRP panel.

5. The apparatus of claim 1 , wherein:
the first CFRP panel and the second CFRP panel are offset such that far ends of each of the first CFRP panel and the second CFRP panel overlap in the vertical direction.

6. The apparatus of claim 1 , wherein:
the pins are inserted into one of the first CFRP panel and the second CFRP panel by puncturing through a thickness of one of the first CFRP panel and the second CFRP panel.

7. The apparatus of claim 1 , wherein:
the pins are inserted into a wet layup of one of the first CFRP panel and the second CFRP panel prior to cure of one of the first CFRP panel and the second CFRP panel.

8. The apparatus of claim 1 , wherein:
the pins are cured with one or more of the first CFRP panel and the second CFRP panel.

9. The apparatus of claim 1 , wherein:
the first CFRP panel and the second CFRP panel form a composite structure of an aircraft.

10. The apparatus of claim 9 , wherein:
the composite structure comprises a wing of the aircraft.

11. The apparatus of claim 1 , wherein:
each the pins are individually smaller than the fastener.

12. The apparatus of claim 1 , wherein:
the pins are configured to provide a path for electrical current away from the fastener.

13. The apparatus of claim 1 , wherein:
one or more of the pins have a different length through the first CFRP panel and the second CFRP panel as compared to other ones of the pins.

14. The apparatus of claim 1 , wherein:
one or more of the pins terminate at different end positions within the first CFRP panel and the second CFRP panel as compared to other ones of the pins.

15. The apparatus of claim 1 , wherein:
a material of the pins includes one of carbon, aluminum, and titanium.

16. The apparatus of claim 1 , wherein:
in the area where the first CFRP panel and the second CFRP panel overlap, a number of the pins is greater than a number of fasteners.

17. The apparatus of claim 1 , wherein:
the fastener is configured to mechanically join the first CFRP panel with the second CFRP panel, the pins extend through the first CFRP panel and the second CFRP panel to provide a path for electrical current away from the fastener, and the pins include a longitudinal body that does not mechanically join the first CFRP panel with the second CFRP panel.

18. The apparatus of claim 1 , wherein:
the area where the first CFRP panel and the second CFRP panel overlap includes a single one of the fastener and multiple ones of the pins.

19. The apparatus of claim 1 , wherein:
the pins are distributed throughout the area where the first CFRP panel and the second CFRP panel overlap to spread through-thickness current conduction away from the fastener.

20. The apparatus of claim 1 , wherein:
the fastener is configured to cause the first group of pins to press against the second group of pins.

Assignees

• Boeing Co

Inventors

• Tuck Derek R
• Boettcher Philipp A
• Smith Carson Alexander
• Misciagna David Thomas

Classifications

• B29C66/7212

  characterised by the composition of the fibres · CPC title

• B29C66/1122

  Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence) · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B29C66/43

  Joining a relatively small portion of the surface of said articles (B29C66/45 takes precedence) · CPC title

• B29C65/562

  using extra joining elements, i.e. which are not integral with the parts to be joined (using plastic snap elements B29C65/58; using plastic rivets B29C65/601) · CPC title