Spacecraft high tensile fabric barrier for hot re-entry gases

Patent metadata

Field	Value
Publication number	US-11260995-B2
Application number	US-201816173821-A
Country	US
Kind code	B2
Filing date	Oct 29, 2018
Priority date	Oct 29, 2018
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

A multi-layer shell structure for a vehicle and method of providing a multi-layer shell structure for a vehicle. The multi-layer structure includes a thermal protection system (TPS) layer, a structural layer connected to the TPS layer, and a high tensile fabric barrier layer bonded to the structural layer. Room-temperature-vulcanizing silicone may be used to bond the TPS layer to the structural layer and bond the high tensile fabric barrier layer to the structural layer. The high tensile fabric barrier layer may create a seal on the structural layer. The multi-layer shell structure may include inner shell enclosing a passenger and/or cargo compartment and an annulus between the inner shell and the high tensile fabric barrier layer. The high tensile fabric barrier layer may prohibit entry of gas into the annulus in the event a hole is created through a portion of the multi-layer shell structure.

First claim

What is claimed is:

1. A multi-layer shell structure for a vehicle comprising:
a thermal protection system (TPS) layer;
a structural layer connected to the TPS layer, the structural layer being a honeycomb structure positioned between composite faceplates; and
a high tensile fabric barrier layer bonded to the structural layer, wherein the structural layer is positioned between the high tensile fabric barrier layer and the TPS layer;
an inner shell enclosing a compartment; and
an annulus that surrounds an entire perimeter of the inner shell, wherein the high tensile fabric barrier layer is positioned directly adjacent to the annulus.

2. The multi-layer shell structure of claim 1 , wherein the high tensile fabric barrier layer creates a seal on an exterior of the structural layer.

3. The multi-layer shell structure of claim 1 , wherein the annulus is between an exterior of the inner shell and the high tensile fabric barrier layer, wherein the high tensile fabric barrier layer prohibits an entry of gas into the annulus in the event a hole is created through the TPS layer and the structural layer.

4. The multi-layer shell structure of claim 3 , wherein the high tensile fabric barrier layer continues to prohibit the entry of gas into the annulus up to a temperature of at least 800 degrees Fahrenheit.

5. The multi-layer shell structure of claim 3 , wherein the annulus has a pressure below a pressure exterior of the TPS layer.

6. The multi-layer shell structure of claim 1 , wherein the inner shell comprises aluminum.

7. The multi-layer shell structure of claim 1 , wherein the high tensile fabric barrier layer is bonded to the structural layer via a layer of room-temperature-vulcanizing silicone.

8. The multi-layer shell structure of claim 1 , wherein the high tensile fabric barrier layer has a tensile strength of 3,000 MPa or greater.

9. The multi-layer shell structure of claim 1 , wherein the high tensile fabric barrier layer comprises a plurality of plies of high tensile fabric woven together to form the high tensile fabric barrier layer.

10. The multi-layer shell structure of claim 9 , wherein the high tensile fabric barrier layer comprises at least ten plies of high tensile fabric.

11. The multi-layer shell structure of claim 1 , further comprising a first layer of bonding material and a second layer of bonding material, wherein the first layer of bonding material is positioned between the TPS layer and the structural layer and wherein the second layer of bonding material is positioned between the structure layer and the high tensile fabric barrier layer.

12. A spacecraft comprising:
a multi-layer shell structure having a windward side and a leeward side, wherein the multi-layer shell structure comprises a thermal protection system (TPS) layer and a structural layer connected to the TPS layer, the structural layer being a honeycomb structure positioned between composite faceplates;
an inner shell enclosing a compartment positioned within the multi-layer shell structure;
an annulus that surrounds an entire perimeter of the inner shell;
a plurality of high tensile fabric barrier segments on the windward side of the multi-layer shell structure, wherein each of the plurality of high tensile fabric barrier segments are bonded to the structural layer of the multi-layer shell structure, wherein each of the plurality of high tensile fabric barrier segments are positioned directly adjacent to the annulus, wherein the structural layer is positioned between the TPS layer and the plurality of high tensile fabric barrier segments; and
wherein the plurality of high tensile fabric barrier segments prohibits an entry of gas into the annulus in the event a hole is created through a portion of the multi-layer shell structure.

13. The spacecraft of claim 12 , wherein each of the plurality of high tensile fabric barrier segments creates a seal on an exterior of the structural layer.

14. The spacecraft of claim 13 , wherein room-temperature-vulcanizing silicone bonds each segment of the plurality of high tensile fabric barrier segments to the structural layer.

15. The spacecraft of claim 14 , wherein the annulus has a pressure below a pressure exterior of the TPS layer.

16. The spacecraft of claim 15 , wherein the plurality of high tensile fabric barrier segments are comprised of high tensile yarn woven into high tensile fabric plies, wherein each of the plurality of high tensile fabric barrier segments comprise multiple high tensile fabric plies woven together to form each of the plurality of high tensile fabric barrier segments.

17. The spacecraft of claim 16 , wherein each of the plurality of high tensile fabric barrier segments comprises at least ten high tensile fabric plies.

18. The spacecraft of claim 12 , wherein the plurality of high tensile fabric barrier segments have a tensile strength of 3,000 MPa or greater.

19. A method of providing a multi-layer shell structure for a vehicle comprising:
coupling a thermal protection system (TPS) layer to a structural layer, the structural layer being a honeycomb structure positioned between composite faceplates;
bonding a high tensile fabric barrier layer to the structural layer, wherein the TPS layer, the structural layer, and the high tensile fabric barrier layer form the multi-layer shell structure enclosing an inner shell enclosing a compartment, wherein the structural layer is positioned between the TPS layer and the high tensile fabric barrier layer; and
providing an annulus between the high tensile fabric barrier layer and the inner shell wherein the high tensile fabric barrier layer is directly adjacent to the annulus, wherein the annulus surrounds an entire perimeter of the inner shell.

20. The method of claim 19 , wherein bonding the high tensile fabric barrier layer to the structural layer further comprises bonding the high tensile fabric barrier layer to the structural layer with room-temperature-vulcanizing silicone.

Assignees

• Boeing Co

Inventors

• Bland Mitchell C

Classifications

• B64G1/62

  Systems for re-entry into the earth's atmosphere; Retarding or landing devices · CPC title

• B64G1/58 Primary

  Thermal protection, e.g. heat shields · CPC title

• B64G1/52

  Protection, safety or emergency devices; Survival aids · CPC title

• B32B15/00

  Layered products comprising {a layer of} metal · CPC title

• B64G1/14

  Space shuttles {(reusable launch rockets B64G1/006)} · CPC title