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:
Mar. 23, 2021

Filed:

Aug. 04, 2017
Applicant:

Space Systems/loral, Llc, Palo Alto, CA (US);

Inventor:

Varouj G. Baghdasarian, Cupertino, CA (US);

Assignee:

Space Systems/Loral, LLC, Palo Alto, CA (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
H01Q 15/14 (2006.01); B64G 1/66 (2006.01); H01Q 3/08 (2006.01); H01Q 1/28 (2006.01); B64G 1/22 (2006.01); B64G 4/00 (2006.01);
U.S. Cl.
CPC ...
H01Q 15/14 (2013.01); B64G 1/222 (2013.01); B64G 1/66 (2013.01); H01Q 1/288 (2013.01); H01Q 3/08 (2013.01); B64G 2004/005 (2013.01);
Abstract

A spacecraft, reconfigurable from a launch configuration to an on-orbit configuration, includes a main body structure, a manipulator, a first deployable rigid reflector and an attachment arrangement, including at least one hold-down assembly (HDA). In the launch configuration, the HDA is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector with the spacecraft main body structure and prevents relative motion between the first reflector and the spacecraft main body. Reconfiguring the spacecraft from the launch configuration to the on-orbit configuration includes (i) actuating the HDA from the fully engaged configuration to a partially engaged configuration; (ii) grasping and moving the first reflector, with the manipulator, a distance in the first direction; and (iii) moving the first reflector from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration.


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