CERAMIC COMPOSITE THERMAL PROTECTION SYSTEM

• US 20140377510A1
• Filed: 05/28/2014
• Published: 12/25/2014
• Est. Priority Date: 01/12/2009
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Pinney, Thomas R., Thatcher, Conley Siddoway, Embler, Jonathan, David, Kaia Elena, Lehman, Leanne L., Zadorozny, Edward A.
• Granted Patent: US 9,248,923 B2
• Time in Patent Office: Days
• US Class Current: 428/192
• 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: Y10T 29/49947 by applying separate fastener
• CPC Class Codes: Y10T 428/24322 Composite web or sheet
• CPC Class Codes: Y10T 428/24777 Edge feature

Abstract

An apparatus comprises a thermal protection element, a number of washers, a ceramic layer, a number of blind fasteners, and a number of tabs. The thermal protection element has an upper surface, a lower surface, and a plurality of sides. The ceramic layer covers at least the plurality of sides of the thermal protection element. The number of tabs is connected to the number of sides by the number of blind fasteners secured to the ceramic layers. The tabs may be part of a frame secured to a groove around the plurality of sides.

Claims

1-11. -11. (canceled)

12. An apparatus comprising:

a thermal protection element having an upper surface, a lower surface, and a plurality of sides;

a groove formed in the plurality of sides of the thermal protection element; and

a frame having an inner edge and a number of tabs opposite of the inner edge, wherein the inner edge of the frame is secured to the groove.

13. The apparatus of claim 12 further comprising:

a ceramic layer covering at least the plurality of sides of the thermal protection element, wherein the ceramic layer conforms to the groove and wherein the inner edge contacts the ceramic layer within the groove.

14. The apparatus of claim 12, wherein the frame comprises:

a number of sections;

a number of brackets; and

a number of rivets capable of securing the number of sections and the number of brackets.

15. The apparatus of claim 12, wherein the inner edge of the frame is fastened to the groove with a compressive load.

16. The apparatus of claim 12, wherein the thermal protection element is comprised of a ceramic material.

17. The apparatus of claim 12 further comprising:

a number of fastening elements each having an end capable of being secured to a structure and having a coupling feature capable of being secured to a corresponding tab in the number of tabs.

18. The apparatus of claim 17, wherein the number of fastening elements comprises a number of posts, wherein an end of each post in the number of posts is capable of being secured to a surface of the structure such that the number of posts extends substantially perpendicular to the surface and wherein the coupling feature is capable of being secured within a hole in the corresponding tab in the number of tabs.

19. The apparatus of claim 17, wherein the structure is for an object selected from one of a mobile platform, an aircraft, a tank, a personnel carrier, a train, a spacecraft, a submarine, a satellite, a rocket, an engine, an engine structure, and an automobile.

20-23. -23. (canceled)

24. A method for securing a thermal protection element to a structure, the method comprising:

positioning a thermal protection element with respect to a number of fastener elements on a surface of the structure, wherein the thermal protection element has a groove formed in a plurality of sides of the thermal protection element and a frame having an inner edge and a number of tabs opposite of the inner edge, wherein the inner edge of the frame is secured to the groove; and

securing the number of tabs to the number of fastener elements on the surface of the structure.

25. The method of claim 24 further comprising:

forming the substrate for the thermal protection element from a ceramic matrix composite material;

forming the groove in the plurality of sides of the thermal protection element;

placing the inner edge of the frame in the groove; and

attaching the frame to the groove.

26. The method of claim 24 further comprising:

forming a facesheet over the substrate after forming the groove and prior to placing the inner edge of the frame in the groove.