Patent attributes
A method of controlling a spacecraft is provided. The method includes one or more of calculating, by a control device, spacecraft position, attitude, and velocity, the spacecraft including a plurality of blade actuators controlling pitch for a plurality of blades, the plurality of blades extending radially away from a spacecraft core and including material configured to be deflected by solar pressure, receiving mission plan updates for the spacecraft, calculating an updated trajectory based on the position, attitude, velocity, mission plan updates, and past spacecraft behavior, generating maneuver parameters for the spacecraft from the updated trajectory, creating new blade pitch profiles for a plurality of blade actuators, from the maneuver parameters, sending controls corresponding to the new blade pitch profiles to the plurality of blade actuators, and transitioning from current blade pitch profiles to the new blade pitch profiles.
