Seat track assemblies for vibration isolation of floor mounted components

Patent metadata

Field	Value
Publication number	US-11214374-B2
Application number	US-201715658140-A
Country	US
Kind code	B2
Filing date	Jul 24, 2017
Priority date	Aug 1, 2016
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

Aircraft, vibration isolation assemblies, and methods of assembling vibration isolation assemblies are provided. An aircraft includes a vibration isolation assembly. The vibration isolation assembly includes a mounting track, a plate, a clamp block, a vibration isolator, and a support fitting. The mounting track defines a cavity and includes flanges that define an opening to the cavity. The plate is configured to be positioned on the flanges outside of the cavity. The clamp block is configured to be fastened to the plate under the flanges of the mounting track within the cavity. The vibration isolator is configured to be laterally constrained by the clamp block within the cavity. The support fitting is configured to be secured to the vibration isolator outside of the cavity.

First claim

What is claimed is:

1. A vibration isolation assembly, comprising:
a mounting track that defines a cavity and includes flanges that define an opening to the cavity, wherein the flanges define opposing semi-circular slots with alternating narrowed portions and wider portions of the opening;
a plate configured for positioning on the flanges outside of the cavity, the plate comprising a first bore for a first fastener, and the plate comprising a second bore;
a clamp block configured for holding the plate to the mounting track, the clamp block comprising a lower portion disposed in the cavity beneath one of the narrowed portions, and the clamp block configured to receive and engage the first fastener to compress the flanges of the mounting track between the plate and the lower portion of the clamp block;
a vibration isolator positioned in one of the wider portions and configured for lateral constraint by the clamp block within the cavity, the vibration isolator comprising:
a lower portion that is wider than the second bore of the plate, the lower portion of the vibration isolator positioned below the plate and in the cavity such that the plate holds the vibration isolator in place;
an upper portion extending through the second bore of the plate and above the plate;
an elastomer; and
an inner member configured to receive and engage a second fastener; and

a support fitting secured to the inner member of the vibration isolator with the second fastener, the support fitting located outside of the cavity and separated from the clamp block.

2. The vibration isolation assembly of claim 1 , wherein the mounting track further defines a bottom surface of the cavity opposite the flanges, and wherein the vibration isolator is configured for vertical support by the bottom surface.

3. The vibration isolation assembly of claim 2 , wherein the elastomer substantially encapsulates the inner member.

4. The vibration isolation assembly of claim 3 , wherein the inner member includes a post and a lower flange, and wherein the support fitting is configured to couple with the post and the lower flange is configured for support by the bottom surface through the elastomer.

5. The vibration isolation assembly of claim 4 , wherein the inner member further includes an upper flange with a top surface facing away from the elastomer, and wherein the top surface is configured to support the support fitting.

6. The vibration isolation assembly of claim 5 , wherein the post defines a threaded bore configured to receive the second fastener, and wherein the support fitting defines a fitting bore to receive the second fastener and secure the support fitting to the inner member.

7. The vibration isolation assembly of claim 1 , wherein the mounting track is a seat track configured for securing to a floor of an aircraft.

8. The vibration isolation assembly of claim 1 , wherein the mounting track has a substantially c-channel shaped cross section.

9. An aircraft comprising:
a floor; and
a vibration isolation assembly secured to the floor, the vibration isolation assembly comprising:
a seat track that defines a cavity and includes flanges that define an opening to the cavity, wherein the flanges define opposing semi-circular slots with alternating narrowed portions and wider portions of the opening;
a plate positioned on the flanges outside of the cavity, the plate comprising a first bore for a first fastener, and the plate comprising a second bore;
a clamp block fastened to the plate and holding the plate to the mounting track, the clamp block comprising a lower portion disposed in the cavity beneath one of the narrowed portions, and the clamp block configured to receive and engage the first fastener to compress the flanges of the mounting track between the plate and the lower portion of the clamp block;
a vibration isolator positioned in one of the wider portions and laterally constrained by the clamp block within the cavity, the vibration isolator comprising:
a lower portion that is wider than the second bore of the plate, the lower portion of the vibration isolator positioned below the plate and in the cavity such that the plate holds the vibration isolator in place;
an upper portion extending through the second bore of the plate and above the plate;
an elastomer; and
an inner member configured to receive and engage a second fastener; and

a support fitting secured to the inner member of the vibration isolator with the second fastener, the support fitting located outside of the cavity and separated from the clamp block and the floor.

10. The aircraft of claim 9 , wherein the seat track further defines a bottom surface of the cavity opposite the flanges, and wherein the vibration isolator is vertically supported by the bottom surface.

11. The aircraft of claim 10 , wherein the elastomer substantially encapsulates the inner member.

12. The aircraft of claim 11 , wherein the inner member includes a post and a lower flange, and wherein the support fitting is coupled with the post and the lower flange is supported by the bottom surface through the elastomer.

13. The aircraft of claim 12 , wherein the inner member further includes an upper flange with a top surface facing away from the elastomer, and wherein the top surface supports the support fitting and is separated from the plate and the floor.

14. The aircraft of claim 13 , wherein the post defines a threaded bore that receives the second fastener, and wherein the support fitting defines a fitting bore through which the second fastener passes to secure the support fitting to the inner member.

15. The aircraft of claim 9 , wherein the seat track has a substantially c-channel shaped cross section.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Lucas Michael
• Lynch Kristopher P
• Wilson Benjamin Frank
• Jonas Jeffrey

Classifications

• B64D11/0696 Primary

  Means for fastening seats to floors, e.g. to floor rails · CPC title

• B64D11/0619 Primary

  with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash · CPC title