Method of deploying a spacecraft shield in space

• US 9,327,848 B2
• Filed: 06/11/2012
• Issued: 05/03/2016
• Est. Priority Date: 06/11/2012
• Status: Active Grant

• Current Assignee: Bigelow Aerospace
• Original Assignee: Bigelow Aerospace
• Inventors: Bigelow, Robert T.
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Fabula, Michael A
• Application Number:
  US13/507,179
• Publication Number:
  US 20130327894A1
• Time in Patent Office: 1,422 Days
• US Class Current: 1/1
• CPC Class Codes: B64G 1/56 Protection against meteoroids or space debris
• CPC Class Codes: B82Y 30/00 Nanotechnology for materials or surface science, e.g. nanocomposites
• CPC Class Codes: B82Y 40/00 Manufacture or treatment of nanostructures
• CPC Class Codes: Y10S 977/742 Carbon nanotubes, CNTs
• CPC Class Codes: Y10S 977/842 for carbon nanotubes or fullerenes
• CPC Class Codes: Y10S 977/902 Specified use of nanostructure

Abstract

A shield comprised of carbon nanotube materials is used to provide a level of protection to a spacecraft. Shield segments are produced in a facility in space. The segments are transported from the facility to a vicinity of a spacecraft hull. The segments are assembled over the hull to substantially cover an area of the hull.

Claims

1. A method of deploying a shield to provide protection to a hull of a spacecraft against space debris, comprising the steps of:

a) providing at least one receiving type shield segment comprised of carbon nanotubes within a spacecraft,

wherein each receiving type shield segment is in a shape to substantially conform to a segment of an outer surface of a hull of a spacecraft deployed in space,

wherein each receiving type shield segment comprises at least two holes extending from an inner surface to an outer surface of the shield segment,

wherein the at least two holes are disposed at opposite ends of each receiving type shield segment and are each adapted to receive a corresponding hook type structure;

b) providing at least one retaining type shield segment comprised of carbon nanotubes within a spacecraft,

wherein each retaining type shield segment is in a shape to substantially conform to a segment of an outer surface of a hull of a spacecraft deployed in space,

wherein each retaining type shield segment comprises at least two hook type structures disposed at opposite ends of each segment,

wherein each hook type structure is adapted to be received by a corresponding hole in a receiving type shield segment;

c) transporting the receiving and retaining type shield segments from inside to outside the spacecraft in space;

d) placing the receiving and retaining type shield segments in the vicinity of a corresponding area of an outer hull of a spacecraft deployed in space;

e) connecting a hook type structure of a retaining type shield segment through a corresponding hole of a receiving type shield segment such that the retaining and receiving type shield segments are assembled in place with respect to one another; and

f) repeating steps c) through e) until the assembled receiving and retaining shield segments substantially enclose the hull of the spacecraft.