The invention relates to a method for simulating a time-saving
orbit change task for "one-to-many" approach of space targets. A service aircraft adopts a double-pulse
orbit change strategy to sequentially approach each target
satellite, and determines an objective function for the time-saving
orbit change; an optimization level is set, wherein, in the first level, a total orbit change time optimization variable is set; in the second level, an approach
sequence optimization variable is set, and an approach sequence of the service aircraft arriving at the target
satellite is determined by the
variable size; in the third and fourth levels, within the total
time limit range for the service aircraft to complete the approach of all target satellites, a value range of an approach orbit change end time optimization variable for each target
satellite that satisfies both a measurement and control window and an illumination window is determined; and a value range of an approach orbit change
start time optimization variable for each target satellite is determined; in the fifth level, under a given approach sequence, given approach orbit change end time and approach orbit change
start time are optimized according to the objective function to obtain an optimization result; and in accordance with the set optimization
level order, optimization is started by level, and the optimal result is selected from the optimization results to obtain the time-saving orbit change strategy.