US 12,459,675 B2
Maneuvering a spacecraft using an optimized guidance trajectory and model predictive control
Tyson Smith, Logan, UT (US); John Akagi, Logan, UT (US); and Greg Droge, Logan, UT (US)
Filed by Space Dynamics Laboratory, North Logan, UT (US)
Filed on Dec. 4, 2023, as Appl. No. 18/528,385.
Application 18/528,385 is a continuation in part of application No. 18/465,505, filed on Sep. 12, 2023, granted, now 12,304,664.
Application 18/465,505 is a continuation in part of application No. 17/891,968, filed on Aug. 19, 2022, granted, now 12,269,618.
Application 17/891,968 is a continuation in part of application No. 17/689,038, filed on Mar. 8, 2022, granted, now 12,129,051.
Prior Publication US 2024/0124162 A1, Apr. 18, 2024
Int. Cl. B64G 1/24 (2006.01); G06F 30/20 (2020.01); G06F 111/10 (2020.01)
CPC B64G 1/244 (2019.05) [G06F 30/20 (2020.01); G06F 2111/10 (2020.01)] 20 Claims
OG exemplary drawing
 
1. A method comprising:
calculating, by use of a processor, a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation;
iteratively calculating a desired trajectory relative to the virtual point for a given spacecraft of the plurality of spacecraft using a relative orbital elements (ROE) state x of the virtual point and the given spacecraft, wherein model predictive control maintains the given spacecraft within an ROE constraint for a given time interval subject to a fuel consumption; and
in response to determining a drift trajectory of the given spacecraft is outside of a trajectory tolerance of the desired trajectory, maneuvering the given spacecraft to within the trajectory tolerance using a maneuver trajectory determined using the model predictive control.