Load-decoupling attachment system

Patent metadata

Field	Value
Publication number	US-11053030-B2
Application number	US-201816154817-A
Country	US
Kind code	B2
Filing date	Oct 9, 2018
Priority date	Oct 9, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A load-decoupling attachment system is configured to secure a component to a primary structure. The load-decoupling system includes a fore end coupling bracket that is configured to attach to a fore end of the component. A first tie rod is coupled to the fore end coupling bracket. The first tie rod is configured to couple to a first portion of the primary structure. A second tie rod is coupled to the fore end coupling bracket. The second tie rod configured to couple to a second portion of the primary structure. A universal joint mount assembly is configured to couple to an aft end of the component and a third portion of the primary structure.

First claim

What is claimed is:

1. A load-decoupling attachment system that is configured to secure a component to a primary structure, the load-decoupling system comprising:
a fore end coupling bracket that is configured to attach to a fore end of the component;
a first tie rod coupled to the fore end coupling bracket, the first tie rod configured to couple to a first portion of the primary structure;
a second tie rod coupled to the fore end coupling bracket, the second tie rod configured to couple to a second portion of the primary structure; and
a universal joint mount assembly that is configured to couple to an aft end of the component and a third portion of the primary structure.

2. The load-decoupling attachment system of claim 1 , wherein the first tie rod, the second tie rod, and the universal joint mount assembly are configured to attach the component to the primary structure such that loads associated with the component are decoupled from loads associated with the primary structure.

3. The load-decoupling attachment system of claim 1 , wherein the fore end coupling bracket comprises a first lug and a second lug, wherein the first tie rod couples to the first lug, and the second tie rod couples to the second lug.

4. The load-decoupling attachment system of claim 1 , wherein each of the first tie rod and the second tie rod is coupled to a spherical bearing that is received and secured within the first lug and the second lug in the fore end coupling bracket.

5. The load-decoupling attachment system of claim 1 , wherein the universal joint mount assembly comprises:
a mounting bracket having first yoke arms;
an aft end coupling bracket that is configured to attach to the aft end of the component, the aft end coupling bracket having second yoke arms; and
a gimbal frame pivotally coupled to the first yoke arms of the mounting bracket and the second yoke arms of the aft end coupling bracket.

6. The load-decoupling attachment system of claim 1 , wherein the component is an avionics or propulsion component of a vehicle, and wherein the primary structure is a frame within the vehicle.

7. The load-decoupling attachment system of claim 1 , wherein each of the first tie rod and the second tie rod comprises a longitudinal support beam that securely retains a first coupling clevis at a first end and a second coupling clevis at a second end that is opposite from the first end, wherein each of the first coupling clevis and the second coupling clevis is coupled to a spherical bearing that is received and secured within the first lug and the second lug in the fore end coupling bracket.

8. The load-decoupling attachment system of claim 1 , further comprising:
a first mounting protuberance that is configured to couple the first tie rod to the first portion of the primary structure; and
a second mounting protuberance that is configured to couple the second tie rod to the second portion of the primary structure.

9. The load-decoupling attachment system of claim 8 , wherein each of the first mounting protuberance and the second mounting protuberance comprises a panel and a fin extending from the panel, wherein a channel is formed through the fin, and wherein the channel retains a spherical bearing of a coupling clevis of one of the first tie rod or the second tie rod.

10. The load-decoupling attachment system of claim 1 , wherein the first tie rod and the second tie rod connect to the fore end coupling bracket at an angle therebetween.

11. The load-decoupling attachment system of claim 1 , wherein longitudinal axes of the first tie rod and the second tie rod are not longitudinally aligned.

12. A load-isolating system comprising:
a primary structure;
a component; and
a load-decoupling attachment system that connects the component to the primary structure, the load-decoupling system comprising:
a fore end coupling bracket attached to a fore end of the component;
a first tie rod coupled to the fore end coupling bracket and a first portion of the primary structure;
a second tie rod coupled to the fore end coupling bracket and a second portion of the primary structure; and
a universal joint mount assembly coupled to an aft end of the component and a third portion of the primary structure,
wherein the first tie rod, the second tie rod, and the universal joint mount assembly attach the component to the primary structure such that loads associated with the component are decoupled from loads associated with the primary structure.

13. The load-isolating system of claim 12 , wherein the fore end coupling bracket comprises a first lug and a second lug, wherein the first tie rod couples to the first lug, and the second tie rod couples to the second lug.

14. The load-isolating system of claim 12 , wherein each of the first tie rod and the second tie rod is coupled to a spherical bearing that is received and secured within the first lug and the second lug in the fore end coupling bracket.

15. The load-isolating system of claim 12 , wherein the universal joint mount assembly comprises:
a mounting bracket having first yoke arms;
an aft end coupling bracket attached to the aft end of the component, the aft end coupling bracket having second yoke arms; and
a gimbal frame pivotally coupled to the first yoke arms of the mounting bracket and the second yoke arms of the aft end coupling bracket.

16. The load-isolating system of claim 12 , wherein the component is an avionics or propulsion component of a vehicle, and wherein the primary structure is a frame within the vehicle.

17. The load-isolating system of claim 12 , wherein each of the first tie rod and the second tie rod comprises a longitudinal support beam that securely retains a first coupling clevis at a first end and a second coupling clevis at a second end that is opposite from the first end, wherein each of the first coupling clevis and the second coupling clevis is coupled to a spherical bearing that is received and secured within the first lug and the second lug in the fore end coupling bracket.

18. The load-isolating system of claim 12 , further comprising:
a first mounting protuberance that couples the first tie rod to the first portion of the primary structure; and
a second mounting protuberance that couples the second tie rod to the second portion of the primary structure,
wherein each of the first mounting protuberance and the second mounting protuberance comprises a panel and a fin extending from the panel, wherein a channel is formed through the fin, and wherein the channel retains a spherical bearing.

19. The load-isolating system of claim 12 , wherein the first tie rod and the second tie rod connect to the fore end coupling bracket at an angle therebetween.

20. The load-isolating system of claim 12 , wherein longitudinal axes of the first tie rod and the second tie rod are not longitudinally aligned.

Assignees

• Boeing Co

Inventors

• Weathers Jeffrey W
• Behel Kraig A
• Ullom Mark W

Classifications

• B64G1/641 Primary

  Interstage or payload connectors (docking systems B64G1/646) · CPC title

• B64G1/4021

  Tank construction; Details thereof · CPC title

• F16B7/04

  Clamping or clipping connections (friction-grip releasable fastenings in general F16B2/00) · CPC title

• B64G1/40

  Arrangements or adaptations of propulsion systems · CPC title