The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Jun. 30, 2020

Filed:

Jun. 29, 2016
Applicant:

Lockheed Martin Corporation, Bethesda, MD (US);

Inventors:

Vadim Khayms, Sunnyvale, CA (US);

Steven W. Sinton, Palo Alto, CA (US);

Peter V. Bedworth, Los Gatos, CA (US);

Assignee:

LOCKHEED MARTIN CORPORATION, Bethesda, MD (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64G 1/10 (2006.01); B64G 1/22 (2006.01); B64G 1/40 (2006.01); B64G 1/44 (2006.01); B64G 1/58 (2006.01); B64G 1/66 (2006.01);
U.S. Cl.
CPC ...
B64G 1/226 (2013.01); B64G 1/10 (2013.01); B64G 1/40 (2013.01); B64G 1/443 (2013.01); B64G 1/58 (2013.01); B64G 1/66 (2013.01);
Abstract

Functional components of spacecraft structures can be subject to detrimental impacts by energetic particles produced from an electric propulsion system. A graphene coating applied to a functional component can maintain electrical conductivity upon a surface of the functional component, thereby allowing charge dissipation to take place, while also resisting sputtering erosion resulting from impacts of the energetic particles. Accordingly, spacecraft structures can include an electric propulsion system, a functional component that is at least partially impacted by an outflow of the electric propulsion system, and a graphene coating upon the functional component. Methods for operating such spacecraft structures can include generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, and at least partially impacting the outflow of energetic particles upon a functional component of the spacecraft structure, where the functional component has a graphene coating thereon.


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