Material assembly for an inflatable aerodynamic braking device for spacecraft deceleration and the like

• US 6,264,144 B1
• Filed: 03/08/2000
• Issued: 07/24/2001
• Est. Priority Date: 08/03/1999
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Thornton, Janine M.
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US09/520,533
• Time in Patent Office: 503 Days
• Field of Search: 244/158.R, 244/158.A, 244/160, 244/113, 428/920, 428/902, 428/408, 428/422, 428/433, 428/436
• US Class Current: 244/159.2
• CPC Class Codes: B64G 1/2227 Inflating
• 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

Abstract

The invention is a material for use in an inflatable aerodynamic braking device for a spacecraft. In detail, the invention includes a plurality of high temperature resistant barrier outer layers. Preferably, the outer layer is made of Aluminoborosilicate fabric. At least one carbon cloth layer is disposed behind said outer layers. A plurality of thermal radiation barrier intermediate layers are disposed behind the at least one carbon cloth layer. The intermediate layers include a plurality of metal foil layers, at least one additional carbon cloth layer interspersed between the metal foil layers. A plurality of metal-coated polymeric layers are disposed behind the metal foil layers, preferably a polyimide fabric coated with Aluminum. The metal foil layers are Aluminum and Titanium. At least one inflatable gas barrier interior layer is disposed behind the intermediate layers, preferably made of a polyimide material. The outer, intermediate and interior layers are sewn together by high temperature resistant thread, preferably Silicon Carbide thread.

Claims

1. A material assembly for use in an inflatable aerodynamic braking device for a spacecraft comprising:

a plurality of high temperature resistant barrier outer layers;

a least one carbon cloth layer disposed behind said outer layers;

a plurality of thermal radiation barrier intermediate layers disposed behind said at least one carbon cloth layer, said intermediate layers comprising;

a plurality of metal foil layers;

at least one additional carbon cloth layer interspersed between said metal foil layers;

a plurality polymeric-layers behind said metal foil layers, said polymeric layers metal coated on at least one side; and

at least one inflatable gas barrier interior layer disposed behind said intermediate layers; and

said outer, intermediate and interior layers joined together at the periphery.

2. The material assembly as set forth in claim 1 wherein said plurality of high temperature resistant barrier outer layers comprises aluminoborsilicate fabric.

3. The material assembly as set forth in claim 1 wherein said metal foil layers include at least one layer of Aluminum foil.

4. The material assembly as set forth in claim 3 wherein said metal foil layers include at least one layer of Titanium foil.

5. The material assembly as set forth in claim 1 wherein said metal coated polymeric layers are made of an Aluminum coated polyimide layer.

6. The material assembly as set forth in claim 1 wherein said at least one inflatable gas barrier interior layer is a polyimide fabric.

7. The material assembly as set forth in claim 1, or 2, or 3, or 4, or 5, or 6, wherein said outer, intermediate and interior layers joined together at the periphery by a sewn joint.

8. The material assembly as set forth in claim 7, wherein said sewn joint is accomplished using a thread made of Silicon Carbide.