Stand-off panel thermal protection system and method of fabricating the same

Patent metadata

Field	Value
Publication number	US-10913552-B2
Application number	US-201715803625-A
Country	US
Kind code	B2
Filing date	Nov 3, 2017
Priority date	Jun 12, 2015
Publication date	Feb 9, 2021
Grant date	Feb 9, 2021

Abstract

A stand-off panel thermal protection system is disclosed. The system comprises a sandwich panel comprising: a first ceramic matrix composite facesheet and a second ceramic matrix composite facesheet. A ceramic matrix composite core is positioned between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet. The ceramic matrix composite core has a perimeter. The first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet extend past the perimeter to form a gap between the first ceramic matrix composite facesheet and the second ceramic matrix composite facesheet surrounding the ceramic matrix composite core. A plurality of orifices are formed through the sandwich panel. The thermal protection system further comprises a soft goods seal positioned in the gap; a plurality of insulation components; a plurality of stand-off brackets; and a plurality of fasteners positionable through the plurality of orifices to couple the sandwich panel to the plurality of brackets.

First claim

What is claimed is:

1. A flight vehicle fastener comprising:
a head;
a shaft attached to the head, the shaft being configured for attachment to a nut, the head and the shaft forming a bolt;
the nut;
a reinforcing insert positionable on the shaft, the reinforcing insert comprising a ceramic;
a washer positionable on the shaft; and
a nut retainer configured to hold the nut in place when the flight vehicle fastener is used to attach a thermal protection system to a flight vehicle,
wherein the bolt, nut and washer comprise a whisker-reinforced alumina ceramic matrix composite, and further wherein the flight vehicle fastener has the ability to withstand temperatures of up to 2400° F. without the need for a panel plug to protect the flight vehicle fastener.

2. The flight vehicle fastener of claim 1 , wherein the whisker-reinforced alumina ceramic matrix composite comprises SiC whiskers at a concentration of about 30% by weight.

3. The flight vehicle fastener of claim 1 , wherein the whisker-reinforced alumina ceramic matrix composite has a melting point of about 3700° F. and a density of about 3.74 g/cc.

4. The flight vehicle fastener of claim 1 , wherein the head comprises grooves for receiving tabs of a cup washer locking mechanism, the grooves configured to prevent the flight vehicle fasteners from rotating when the tabs are positioned therein.

5. The flight vehicle fastener system of claim 1 , wherein the nut retainer comprises a nickel superalloy metallic material.

6. A method of attaching a thermal protection system to a flight vehicle, the method comprising:
positioning a plurality of fasteners through a plurality of orifices formed through the thermal protection system, and
coupling the thermal protection system to the flight vehicle using the plurality of fasteners, the fasteners comprising a ceramic material,
wherein the fasteners comprise:
a head;
a shaft attached to the head, the shaft being configured for attachment to a nut, the head and the shaft forming a bolt;
the nut;
a reinforcing insert positionable on the shaft, the reinforcing insert comprising a ceramic;
a washer positionable on the shaft; and
a nut retainer configured to hold the nut in place when the fastener is used to attach the thermal protection system to the flight vehicle,
wherein the bolt, nut and washer comprise the ceramic material, the ceramic material comprising a whisker-reinforced alumina ceramic matrix composite, and further wherein the fastener has the ability to withstand temperatures of up to 2400° F. without the need for a panel plug to protect the fasteners and without significant degradation in strength and stiffness properties.

7. The method of claim 6 , wherein the flight vehicle is a rocket, an aircraft or a spacecraft.

8. The method of claim 6 , wherein the whisker-reinforced alumina ceramic matrix composite comprises SiC whiskers at a concentration of about 30% by weight.

9. The method of claim 6 , wherein the whisker-reinforced alumina ceramic matrix composite has a melting point of about 3700° F. and a density of about 3.74 g/cc.

10. The method of claim 6 , wherein a head of the fasteners comprises grooves for receiving tabs of a cup washer locking mechanism, the method further comprising positioning the tabs of the cup washer into the grooves to prevent the fasteners from rotating.

11. The method of claim 6 , wherein the nut retainer comprises a nickel superalloy metallic material.

12. A flight vehicle fastener system comprising:
a head;
a shaft attached to the head, the head and the shaft forming a bolt;
a stand-off bracket positionable on the shaft, the standoff bracket comprising a ceramic;
a washer positionable on the shaft;
a nut configured for attachment to the shaft; and
a nut retainer configured to hold the nut in place when the flight vehicle fastener is used to attach a thermal protection system to a flight vehicle;
wherein the bolt, nut and washer comprise a whisker-reinforced alumina ceramic matrix composite, and further wherein the flight vehicle fastener has the ability to withstand temperatures of up to 2400° F. without the need for a panel plug to protect the flight vehicle fastener.

13. The flight vehicle fastener system of claim 12 , wherein the stand-off bracket comprises a ceramic matrix composite material or high temperature metallic material.

14. The flight vehicle fastener system of claim 12 , wherein the stand-off bracket comprises alumina.

15. The flight vehicle fastener system of claim 12 , wherein the flight vehicle fastener further includes a reinforcing insert positionable on the shaft.

16. The flight vehicle fastener system of claim 12 , wherein the whisker-reinforced alumina ceramic matrix composite comprises SiC whiskers at a concentration of about 30% by weight.

17. The flight vehicle fastener system of claim 16 , wherein the whisker-reinforced alumina ceramic matrix composite has a melting point of about 3700° F. and a density of about 3.74 g/cc.

18. The flight vehicle fastener system of claim 17 , wherein the head comprises grooves for receiving tabs of a cup washer locking mechanism, the grooves configured to prevent the flight vehicle fasteners from rotating when the tabs are positioned therein.

19. The flight vehicle fastener system of claim 12 , wherein the whisker-reinforced alumina ceramic matrix composite has a melting point of about 3700° F. and a density of about 3.74 g/cc.

20. The flight vehicle fastener system of claim 12 , wherein the nut retainer comprises a nickel superalloy metallic material.

Assignees

• Boeing Co

Inventors

• Best Michael J
• Pinney Thomas R
• Embler Jonathan D

Classifications

• B64G1/62

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

• F16B33/006

  Non-metallic fasteners using screw-thread · CPC title

• B32B3/08 Primary

  characterised by added members at particular parts {(layer formed of separate pieces of material which are juxtaposed side-by-side B32B3/14, B32B3/18)} · CPC title

• B64G1/14

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

• B32B2250/03

  3 layers · CPC title