The invention relates to a common ground trajectory giant
constellation fly-over
orbit optimization method, device and equipment, and relates to the technical field of
spaceflight. The method comprises the steps of obtaining task initial parameters; establishing an
orbit optimization model; traversing different fly-over initial moments of a first target
satellite in the whole task to obtain a maneuver-free fly-over nominal
orbit and a corresponding target
satellite fly-over number; deriving a plurality of maneuver-free flyover orbits for accessing the whole
constellation; establishing a multi-pulse transfer optimization model, and solving the optimal speed increment of each transfer type; mapping each maneuver-free flyover track into an access node, constructing a node transfer
cost matrix according to the optimal speed increment, and solving an optimal access sequence for accessing all nodes; and integrating the parameters of a plurality of maneuver-free flyover orbits, the optimal access sequence and the maneuver scheme of each transfer type to form a most economical
propellant flyover scheme for accessing the whole common ground trajectory giant
constellation. According to the method,
multiple target satellites can fly over through one-time maneuvering, and efficiency and fuel economy are both considered.