STAND-OFF PANEL THERMAL PROTECTION SYSTEM AND METHOD OF FABRICATING THE SAME

• US 20180057192A1
• Filed: 11/03/2017
• Published: 03/01/2018
• Est. Priority Date: 06/12/2015
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: BEST, Michael J., PINNEY, Thomas R., EMBLER, Jonathan D.
• Granted Patent: US 10,913,552 B2
• Time in Patent Office: Days
• CPC Class Codes: B64G 1/14 Space shuttles reusable launch rockets B64G1/006
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices
• CPC Class Codes: F16B 33/006 Non-metallic fasteners using screw-thread

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.

Claims

1. A flight vehicle fastener comprising:

a head; and

a shaft attached to the head, the shaft being configured for attachment to a nut,

wherein the fastener comprises a ceramic material.

2. The fastener of claim 1, wherein the ceramic material comprises alumina.

3. The fastener of claim 1, wherein the ceramic material comprises a whisker-reinforced alumina ceramic matrix composite.

4. The fastener of claim 3, wherein the whisker-reinforced alumina ceramic matrix composite comprises SiC whiskers at a concentration of about 30% by weight.

5. The fastener of claim 3, 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.

6. The fastener of claim 1, wherein the fastener is a ceramic bolt.

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

8. The fastener of claim 1, wherein the fastener further comprises a nut and a nut retainer configured to hold the nut in place when the fastener is used to attach a thermal protection system to the flight vehicle.

9. The fastener of claim 1, wherein the fastener has the ability to withstand temperatures of up to 2400°

F. without the need for panel plugs or other features to protect the fasteners and without significant degradation in strength and stiffness properties.

10. The fastener of claim 1, wherein the fastener has the ability to withstand temperatures of up to 2400°

F.

11. A method of attaching a thermal protection system to a flight vehicle, the method comprising:

positioning a plurality of fasters 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.

12. The method of claim 11, wherein the flight vehicle is a rocket, an aircraft or a spacecraft.

13. The method of claim 11, wherein the ceramic material comprises alumina.

14. The method of claim 11, wherein the ceramic material comprises a whisker-reinforced alumina ceramic matrix composite.

15. The method of claim 14, wherein the whisker-reinforced alumina ceramic matrix composite comprises SiC whiskers at a concentration of about 30% by weight.

16. The method of claim 14, 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.

17. The method of claim 11, wherein the fasteners comprise ceramic bolts.

18. The method of claim 11, wherein the fasteners each further comprise a nut and a nut retainer, the method further comprising holding the nut in place with the nut retainer when coupling the thermal protection system to the flight vehicle.

19. The method of claim 11, 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.

20. The method of claim 11, wherein the fastener has the ability to withstand temperatures of up to 2400°

F. without the need for panel plugs or other features to protect the fasteners and without significant degradation in strength and stiffness properties.