The invention discloses a calculation method of a maneuvering window of a relative navigation tributary satellite. The method comprises the following steps: calculating an orbital transition speed increment and a relative speed when interacting with a companion star of a main star at a specified ignition timing and an orbital transition time according to the position and the velocity parameters ofthe main star and the companion star; setting the ignition timing range and the orbital transition time range of the main star, taking the ignition timing as the abscissa and the orbital transition time as the ordinate, so as to obtain a velocity increment when the main star accelerates and a velocity contour map relative to the companion star when interacting with the companion star; and obtaining the ignition timing and the orbital transition time satisfying a main star orbital velocity increment constraint according to the velocity contour map. In addition, according to the velocity contour map, the maneuvering window with the optimal incremental speed and the optimal orbit transition time of the main star can be obtained. The invention can also obtain the direction and speed incrementrequirements of the main star ignition and the speed and direction of the relative companion when interacting with the companion star according to the specified ignition timing and the orbit transition time.