In-situ passivation and insulation layer for a flexible thermal protection system (FTPS)

Patent metadata

Field	Value
Publication number	US-10934028-B2
Application number	US-201715813997-A
Country	US
Kind code	B2
Filing date	Nov 15, 2017
Priority date	Nov 15, 2016
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A lightweight flexible BNNT mat or fabric provides improved thermal stability and shielding capabilities under a hypersonic thermal flux. The BNNT mat reduces the stagnation temperature and maintains a low regression rate. An in-situ passivation layer may be formed on the BNNT mat or fabric under high thermal flux. The passivation layer minimizes or prevents penetration of the atmosphere (air or gas) as well as heat and radiation through the thickness of the BNNT material, and it effectively diffuses heat throughout the mat or fabric laterally and radially to minimize localized excessive heat. A BNNT mat according to the present disclosure may also efficiently transfer heat from the BNNT material via radiation due to the high thermal emissivity (0.92) of the BNNT material.

First claim

What is claimed is:

1. A method of providing a thermal barrier, the method comprising:
positioning a layer of material comprising boron nitride nanotubes (BNNT) adjacent at least a portion of a surface to be shielded from thermal energy, wherein the layer of material further comprises elemental particles disposed in the BNNT adjacent to an outer exposed surface of the layer of material that is opposite the surface to be shielded from thermal energy, wherein the elemental particles react with the BNNT when the outer exposed surface of the layer of material is exposed to a high temperature gas or a thermal load greater than about 300 degrees Celsius during use to form a refractory material in a passivation and insulation sublayer of the layer of material during use, wherein the passivation and insulation sublayer formed during use is disposed adjacent to the outer exposed surface of the layer of material, and wherein the refractory material of the passivation and insulation sublayer comprises boron oxide, boron carbide, or boron oxide and boron carbide to provide 1) in-situ heat passivation, 2) a gas barrier, or 3) in-situ heat passivation and a gas barrier that minimizes transmission of heat and/or radiation further into the layer of material and into the surface to be shielded from thermal energy.

2. The method of claim 1 , wherein the layer of material comprises a mat.

3. The method of claim 1 , wherein the BNNT are configured to form a gas barrier when the layer of material is exposed to the high temperature gas.

4. The method of claim 1 , wherein the layer of material comprises a BNNT mat having a thickness of about 0.5 mm to about 20 mm.

5. The method of claim 4 , wherein the BNNT mat has a density of about 0.15 g/cm 3 to about 2.52 g/cm 3 .

6. The method of claim 1 , further comprising forming an inflatable structure from the layer of material.

7. The method of claim 1 , further comprising utilizing front and back sides of the layer of material to manage a thermal load.

8. The method of claim 1 , wherein the layer of material is fire resistant.

9. The method of claim 1 , further comprising attaching the layer of material to a space vehicle to provide thermal shielding for atmospheric re-entry.

10. The method of claim 1 , wherein the elemental particles comprise carbon particles.

11. The method of claim 1 , wherein the elemental particles comprise titanium, hafnium, or nitrogen nanoparticles, or a combination thereof.

12. The method of claim 1 , wherein the passivation and insulation sublayer is formed upon exposure of the layer of material to the high temperature during use.

13. A method of providing aerothermal shielding of a space vehicle during planetary re-entry and descent, the method comprising:
providing at least one layer of flexible aerothermal shielding material comprising a non-woven mat of boron nitride nanotubes (BNNT) including elemental particles disposed in the BNNT adjacent to an outer exposed surface of the layer of material, wherein the elemental particles react with the BNNT when the outer exposed surface of the layer of material is exposed to a high temperature gas or a thermal load greater than about 300 degrees Celsius to form a refractory material in a passivation and insulation sublayer of the layer of material, wherein the passivation and insulation sublayer is disposed adjacent to the outer exposed surface of the layer of material, and wherein the refractory material of the passivation and insulation sublayer comprises boron oxide, boron carbide, or boron oxide and boron carbide to provide aerothermal shielding that minimizes transmission of heat and/or radiation further into the layer of material;
forming a flexible thermal protection system (FTPS) from the non-woven mat of BNNT and elemental particles;
securing the FTPS to the space vehicle; and
configuring the FTPS to be deployed prior to or during planetary re-entry and descent of the space vehicle,
wherein in use the FTPS deploys with the outer exposed surface facing outward so that it is exposed to the high temperatures to form the insulation sublayer to minimize transmission of heat and/or radiation to the space vehicle.

14. The method of claim 13 , wherein the non-woven mat of BNNT has a thickness of about 0.5 to about 20 mm.

15. The method of claim 13 , wherein the non-woven mat of BNNT has a density of about 0.15 g/cm 3 to about 2.52 g/cm 3 .

16. A method of providing a thermal barrier, the method comprising:
providing a layer of material comprising boron nitride tubes (BNNT); and
disposing elemental particles in the BNNT adjacent to first and second opposite surfaces of the layer of material,
wherein the elemental particles react with the BNNT when the layer of material is exposed to a high temperature gas or a thermal load greater than about 300 degrees Celsius during use to form a refractory material in first and opposite second passivation and insulation sublayers of the layer of material during use, wherein the first and second passivation and insulation sublayers are disposed adjacent to the respective first and second surfaces of the layer of material with a core sublayer of the material between them, and wherein the refractory material of the passivation and insulation sublayers comprises boron oxide, boron carbide, or boron oxide and boron carbide to provide 1) in-situ heat passivation, 2) a gas barrier, or 3) in-situ heat passivation and a gas barrier that minimizes transmission of heat and/or radiation through the layer of material.

17. The method of claim 16 , wherein the refractory material comprises boron oxide.

18. The method of claim 16 , wherein the refractory material comprises boron carbide.

19. The method of claim 16 , wherein the refractory material comprises a ceramic.

20. The method of claim 16 , wherein the layer of material comprises a mat.

Assignees

• Nasa

Inventors

• Hocker John-Andrew S
• Park Cheol
• Chu Sang-Hyon
• Kang Jin Ho
• Fay Catharine C

Classifications

• B64G1/62 Primary

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

• C01B21/064 Primary

  with boron · CPC title

• C01P2006/37

  Stability against thermal decomposition · CPC title

• B64G1/58

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

• C01P2004/13

  Nanotubes · CPC title