Lightning protection in aircrafts constructed with carbon fiber reinforced plastic

Patent metadata

Field	Value
Publication number	US-11767128-B2
Application number	US-202217682141-A
Country	US
Kind code	B2
Filing date	Feb 28, 2022
Priority date	Dec 11, 2017
Publication date	Sep 26, 2023
Grant date	Sep 26, 2023

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. A composite structure for an aircraft, the composite structure comprising:
a plurality of Carbon Fiber Reinforced Plastic (CFRP) panels that are horizontally adjacent with one another, each CFRP panel including:
an upper surface having a mesh foil;
a fastener inserted through the CFRP panel in a vertical direction, the fastener configured to secure the CFRP panel to a metallic frame of the aircraft located proximate to a lower surface of the CFRP panel; and
a plurality of electrically conductive pins extending in the vertical direction to electrically connect the mesh foil and the metallic frame of the aircraft.

2. The composite structure of claim 1 , wherein:
the pins are configured to extend beyond the lower surface of the CFRP panel prior to tightening the fastener and do not contact the metallic frame of the aircraft prior to tightening the fastener; and
the pins are configured to contact the metallic frame of the aircraft after tightening the fastener.

3. The composite structure of claim 1 , wherein:
the pins are configured to puncture the CFRP panels.

4. The composite structure of claim 1 , wherein:
the composite structure comprises a wing of the aircraft.

5. The composite structure of claim 1 , wherein:
the pins are parallel with the fastener and perpendicular to composite layers of each of the CFRP panels.

6. The composite structure of claim 1 , further comprising:
another plurality of electrically conductive pins extending horizontally in a direction perpendicular to the vertical direction to electrically connect adjacent ones of the CFRP panels.

7. The composite structure of claim 1 , wherein:
the fastener is configured to mechanically join a CFRP panel with the metallic frame, the pins extend through the 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 CFRP panel with the metallic frame.

8. The composite structure of claim 1 , wherein:
the pins are distributed within an area of a CFRP panel to spread through-thickness current conduction away from the fastener.

9. The composite structure of claim 1 , wherein:
each of the pins is individually smaller than the fastener.

10. The composite structure of claim 1 , wherein:
a material of the pins includes one of carbon, aluminum, and titanium.

11. The composite structure of claim 1 , wherein:
one of the CFRP panels is directly in contact with another of the CFRP panels.

12. The composite structure of claim 1 wherein:
each of the pins is distinct from others of the pins.

13. The composite structure of claim 1 wherein:
a diameter of each of the pins is less than a diameter of the fastener.

14. The composite structure of claim 1 wherein:
the CFRP panels are co-cured with the pins.

15. The composite structure of claim 1 wherein:
layers of the CFRP panels exhibit anisotropic conductivity.

16. The composite structure of claim 1 wherein:
multiple ones of the pins surround a single fastener.

17. A composite structure for an aircraft, the composite structure comprising:
a plurality of Carbon Fiber Reinforced Plastic (CFRP) panels that are horizontally adjacent with one another, wherein neighboring CFRP panels are in direct contact with each other, each CFRP panel including:
an upper surface having a mesh foil;
a fastener inserted through the CFRP panel in a vertical direction, the fastener configured to secure the CFRP panel to a metallic frame of the aircraft, located proximate to a lower surface of the CFRP panel; and
a plurality of distinct electrically conductive pins extending in the vertical direction to electrically connect the mesh foil and the metallic frame of the aircraft, wherein a diameter of each of the pins is less than a diameter of the fastener.

18. A composite structure for an aircraft, the composite structure comprising:
a plurality of composite panels that form a wing of the aircraft, wherein the composite panels are horizontally adjacent with one another, each composite panel including:
an upper surface having a metal mesh;
a fastener inserted through the composite panel in a vertical direction, the fastener configured to secure the composite panel to a frame of the aircraft located proximate to a lower surface of the composite panel; and
a plurality of electrically conductive pins extending in the vertical direction to electrically connect the upper surface of the composite panel and the frame of the aircraft.

19. The composite structure of claim 18 , wherein:
the pins are parallel with the fastener and perpendicular to composite layers of each of the composite panels.

20. The composite structure of claim 18 , further comprising:
another plurality of electrically conductive pins extending horizontally in a direction perpendicular to the vertical direction to electrically connect adjacent ones of the composite panels.

Assignees

• Boeing Co

Inventors

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

Classifications

• B64D45/02 Primary

  Lightning protectors; Static dischargers · 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

• B29C66/1122

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

• B29C66/43

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

• B29C66/7212

  characterised by the composition of the fibres · CPC title