Algorithms are developed to find optimal guidance for an inspector satellite operating nearby a resident space object (RSO). For a non-maneuvering RSO, methods are first developed for a satellite subject to maximum slew rates toconduct an initial inspection of an RSO, where the control variables include the throttle level and direction of the thrust. Second, methods are developed to optimally maneuver a satellite with on/off thrusters into a natural motion circumnavigation or teardrop trajectory, subject to lighting and collision constraints. It is shown that for on/off thrusters, a control sequence can be parameterized to a relatively small amount of control variables and the relative states can be analytically propagated as a function of those control variables. For a maneuvering RSO, differential games are formulated and solved for an inspector satellite to achieve multiple inspection goals, such as aligning with the Sun vector or matching the RSO's energy. The developed algorithms lead to fuel and time savings which can increase the mission life and capabilities of inspector satellites and thus improve space situational awareness for the U.S. Air Force.
Optimal Finite Thrust Guidance Methods for Constrained Satellite Proximity Operations Inspection Maneuvers
2018
249 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Algorithms , Space objects , Space situational awareness , Artificial satellites , Geosynchronous orbits , Spacecraft , Orbital elements , Air force , Collision avoidance , Equations of motion , Genetic algorithms , Boundary value problems , Satellite rendezvous and proximity operations , Optimal control , Trajectory optimization , Path planning , Differential games , Resident space object , Inspector satellite , Natural motion circumnavigation
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