For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method iteratively calculates 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. Model predictive control maintains the given spacecraft within an ROE constraint for a given time interval subject to a fuel consumption. 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.
MANEUVERING A SPACECRAFT USING AN OPTIMIZED GUIDANCE TRAJECTORY AND MODEL PREDICTIVE CONTROL
2024-04-18
Patent
Electronic Resource
English
Maneuvering a spacecraft using an optimized guidance trajectory and model predictive control
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