Embedded tear straps in metal structures

Patent metadata

Field	Value
Publication number	US-10059429-B2
Application number	US-201514696364-A
Country	US
Kind code	B2
Filing date	Apr 24, 2015
Priority date	Apr 24, 2015
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A method comprises embedding tear straps in a metal aircraft structure having a fully formed contour and thickness. The tear straps include strips of fibers that are substantially stronger and stiffer than the metal aircraft structure. The fibers are embedded beneath at least one surface of the metal aircraft structure via ultrasonic consolidation.

First claim

The invention claimed is:

1. A method comprising embedding tear straps in a metal aircraft structure having a fully formed contour and thickness, the tear straps including strips of fibers that are stronger and stiffer than the metal aircraft structure, the strips of fibers embedded beneath at least one surface of the metal aircraft structure with an ultrasonic consolidation end effector, the end effector including a head for depositing the strips of fibers on the at least one surface of the metal aircraft structure, a wheel-shaped horn for applying pressure to the strips of fibers as the strips of fibers are being deposited, and a source for applying ultrasonic vibrations to the wheel-shaped horn.

2. The method of claim 1 , wherein the strips of fibers are at least six times stronger than the metal aircraft structure.

3. The method of claim 1 , wherein the strips of fibers are at least five times stiffer than the metal aircraft structure.

4. The method of claim 1 , wherein the tear straps do not entirely cover the metal aircraft structure.

5. The method of claim 1 , further comprising fully forming the metal aircraft structure prior to embedding the tear straps.

6. The method of claim 1 , wherein the strips of fibers are selected from a group consisting of aramid fibers and ceramic fibers.

7. The method of claim 1 , wherein the strips of fibers of each tear strap are unidirectional and embedded as rovings.

8. The method of claim 7 , wherein the rovings are embedded at least 0.001 inches beneath the at least one surface of the metal aircraft structure.

9. The method of claim 1 , wherein the metal aircraft structure includes a metal aircraft skin; and wherein the strips of fibers are embedded in the metal aircraft skin.

10. The method of claim 9 , wherein a ratio of skin thickness to tear strap thickness is approximately 10:1.

11. The method of claim 9 , wherein the strips of fibers are embedded in inner and outer surfaces of the metal aircraft skin, and wherein embedding pressure and vibrations are applied to the strips of fibers on both surfaces of the metal aircraft skin during the ultrasonic consolidation.

12. The method of claim 9 , wherein the metal aircraft skin includes a metal fuselage skin; and wherein the tear straps extend in circumferential and longitudinal directions in the metal fuselage skin.

13. The method of claim 9 , further comprising assembling the metal aircraft skin to a stiffening substructure after the tear straps have been embedded in the metal aircraft skin.

14. The method of claim 1 , wherein the metal aircraft structure includes a metal aircraft skin that is panelized, and wherein the strips of fibers are embedded beneath inner and outer surfaces of the metal aircraft skin.

15. A system comprising:
a metal aircraft structure;
tear straps including fibers that are stronger and stiffer than the metal aircraft structure; and
an ultrasonic consolidation end effector for embedding the fibers of the tear straps beneath a surface of the metal aircraft structure, the end effector including a head for depositing the fibers on the surface of the metal aircraft structure, a wheel-shaped horn for applying pressure to the fibers as the fibers are being deposited, and a source for applying ultrasonic vibrations to the wheel-shaped horn.

16. The system of claim 15 , wherein the metal aircraft structure includes a metal aircraft skin.

Assignees

• Boeing Co

Inventors

• Nordman Paul S

Classifications

• B64C3/26 Primary

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

• B23K20/2333

  one layer being aluminium, magnesium or beryllium · CPC title

• B23K2201/006

  Operations & Transport · mapped topic

• B64C3/20

  Integral or sandwich constructions · CPC title

• B23K2203/10

  Operations & Transport · mapped topic