US 12,258,307 B2
System for producing remote sensing data from near earth orbit
Ronald E. Reedy, San Diego, CA (US); and Thomas E. Schwartzentruber, San Diego, CA (US)
Assigned to Skeyeon, Inc., San Diego, CA (US)
Filed by Skeyeon, Inc., San Diego, CA (US)
Filed on Nov. 27, 2023, as Appl. No. 18/519,989.
Application 18/519,989 is a continuation of application No. 16/953,450, filed on Nov. 20, 2020, granted, now 11,840,498.
Application 16/953,450 is a continuation of application No. 16/129,210, filed on Sep. 12, 2018, granted, now 10,858,309, issued on Dec. 8, 2020.
Application 16/129,210 is a continuation of application No. 15/868,794, filed on Jan. 11, 2018, granted, now 10,590,068, issued on Mar. 17, 2020.
Application 15/868,794 is a continuation in part of application No. 15/439,533, filed on Feb. 22, 2017, granted, now 10,351,267, issued on Jul. 16, 2019.
Claims priority of provisional application 62/430,727, filed on Dec. 6, 2016.
Prior Publication US 2024/0317677 A1, Sep. 26, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. C07C 259/06 (2006.01); A61P 35/00 (2006.01); B64G 1/10 (2006.01); B64G 1/42 (2006.01); B64G 1/44 (2006.01); G01S 19/39 (2010.01); H04B 7/185 (2006.01); H04B 7/195 (2006.01); B64G 1/66 (2006.01); G01S 13/90 (2006.01)
CPC C07C 259/06 (2013.01) [A61P 35/00 (2018.01); B64G 1/1021 (2013.01); B64G 1/425 (2013.01); B64G 1/443 (2013.01); G01S 19/39 (2013.01); H04B 7/18513 (2013.01); H04B 7/195 (2013.01); B64G 1/1028 (2023.08); B64G 1/1035 (2023.08); B64G 1/66 (2013.01); G01S 13/90 (2013.01)] 21 Claims
OG exemplary drawing
 
1. A satellite configured to maintain an orbit between 100 km and 350 km, the satellite comprising:
a vehicle bus comprising:
an engine configured to generate thrust; and
a frontal section having at least one beveled surface, the at least one beveled surface at least partially coated with a coating material,
wherein the coating material is configured to at least partially specularly reflect incident atmospheric air particles during flight and is atomic-oxygen resistant, and
wherein the at least partially specularly reflecting coating material and the at least one beveled surface are configured to reduce drag on and damage to the satellite from interactions with incident atomic oxygen particles during flight.