Load-transferring connection between structurally loaded components

Patent metadata

Field	Value
Publication number	US-11149770-B2
Application number	US-201816029074-A
Country	US
Kind code	B2
Filing date	Jul 6, 2018
Priority date	Jun 11, 2018
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A system may include a fastener strap, a first component, and a second component. The fastener strap may include a strap section, at least one first stiffening rib section, and at least one second stiffening rib section. The first component may include a first strap section channel and at least one first stiffening rib section channel positioned along the first strap section channel. The second component may include a second strap section channel and at least one second stiffening rib section channel positioned along the second strap section channel. When the fastener strap is installed in the first strap section channel, the at least one first stiffening rib section channel, the second strap section channel, and the at least one second stiffening rib section channel, a load-bearing connection may be formed between the first component and the second component.

First claim

What is claimed is:

1. A system, comprising:
a fastener strap comprising a strap section, two first stiffening rib sections with a first gap between the two first stiffening rib sections, and two second stiffening rib sections with a second gap between the two second stiffening rib sections, the two first stiffening rib sections and the two second stiffening rib sections extending outwardly from a side of the strap section, the two first stiffening rib sections and the two second stiffening rib sections extending longitudinally along portions of the side of the strap section, the two first stiffening rib sections being parallel to the two second stiffening rib sections, wherein the first gap and the second gap are adjacently located along the fastener strap, wherein the fastener strap is more flexible at locations along the first and second gaps than at locations located along the two first stiffening rib sections and the two second stiffening rib sections;
a first composite shell comprising a first strap section channel and two first stiffening rib section channels positioned along the first strap section channel with a first corresponding gap between the two first stiffening rib section channels, the first strap section channel and the two first stiffening rib section channels positioned along at least one edge of the first composite shell, the first strap section channel configured to receive a first portion of the strap section of the fastener strap, the two first stiffening rib section channels configured to receive the two first stiffening rib sections of the fastener strap; and
a second composite shell comprising a second strap section channel and two second stiffening rib section channels positioned along the second strap section channel with a second corresponding gap between the two second stiffening rib section channels, the second strap section channel and the two second stiffening rib section channels positioned along at least one edge of the second composite shell, the second strap section channel configured to receive a second portion of the strap section of the fastener strap, the two second stiffening rib section channels configured to receive the two second stiffening rib sections of the fastener strap,
wherein, when the fastener strap is installed in the first strap section channel, the two first stiffening rib section channels, the second strap section channel, and the two second stiffening rib section channels, a load-bearing connection is formed between the first composite shell and the second composite shell.

2. The system of claim 1 , further comprising attachment means, the fastener strap having first and second ends, the attachment means configured to secure the first and the second ends of the fastener strap against the first composite shell and the second composite shell.

3. The system of claim 1 , wherein the second composite shell is a wing composite shell, a fuselage composite shell, or a rotor section of a drone.

4. The system of claim 1 , wherein the first composite shell is a wing composite shell and the second composite shell is a fuselage composite shell.

5. The system of claim 1 , wherein the first and second gaps allow the fastener strap to bend around corresponding curved sections of the first and second composite shells.

6. The system of claim 1 , further comprising a support frame, the support frame abutting a portion of the first composite shell and a portion of the second composite shell, the support frame configured to support a middle portion of the strap section of the fastener strap.

7. The system of claim 1 , wherein the first composite shell is a wing composite shell, a fuselage composite shell, or a rotor section composite shell of a drone.

8. A system, comprising:
a fastener strap comprising a strap section, at least one first stiffening rib section, and at least one second stiffening rib section, the at least one first stiffening rib section and the at least one second stiffening rib section extending outwardly from a side of the strap section, the at least one first stiffening rib section and the at least one second stiffening rib section extending longitudinally along portions of the side of the strap section, the at least one first stiffening rib section being parallel to the at least one second stiffening rib section;
a panel comprising a first strap section channel and at least one first stiffening rib section channel positioned along the first strap section channel, the first strap section channel and the at least one first stiffening rib section channel positioned along at least one edge of the panel, the first strap section channel configured to receive a first portion of the strap section of the fastener strap, the at least one first stiffening rib section channel configured to receive the at least one first stiffening rib section of the fastener strap;
a component comprising a second strap section channel and at least one second stiffening rib section channel positioned along the second strap section channel, the second strap section channel and the at least one second stiffening rib section channel positioned along at least one edge of the component, the second strap section channel configured to receive a second portion of the strap section of the fastener strap, the at least one second stiffening rib section channel configured to receive the at least one second stiffening rib section of the fastener strap; and
a second fastener strap installed on the panel and the component, the second fastener strap installed on opposite sides of the panel and the component as the fastener strap,
wherein, when the fastener strap is installed in the first strap section channel, the at least one first stiffening rib section channel, the second strap section channel, and the at least one second stiffening rib section channel and when the second fastener strap is installed on the panel and the component, a load-bearing connection is formed between the panel and the component,
wherein the component is a second panel.

9. The system of claim 8 , wherein the at least one first stiffening rib section comprises two first stiffening rib sections with a first gap between the two first stiffening rib sections, wherein the at least one second stiffening rib section comprises two second stiffening rib sections with a second gap between the two second stiffening rib sections, wherein the first gap and the second gap are adjacently located along the fastener strap.

10. The system of claim 8 , wherein the panel is an aircraft interior panel.

Assignees

• Rockwell Collins Inc

Inventors

• Ballocchi Paolo
• Christie Damian

Classifications

• B64U10/25

  Fixed-wing aircraft (VTOL aircraft B64U10/20) · CPC title

• B64U20/65

  Composite materials · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C3/26

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

• F16B5/0621 Primary

  in parallel relationship (fastened by a drive-pin F16B19/1081; fastened by a device locking by rotation F16B21/02) · CPC title