The invention relates to an interplanetary
transfer orbit design method, in particular to a
transfer orbit design method from a periodical
orbit which is near
dynamic balance points of a three-
body system to a small
celestial body and belongs to the technical field of
aerospace. Firstly, based on the periodical
orbit which is near the
dynamic balance points of the three-
body system where a
detector is located, an initial state of the
detector x0=[ r0, v0] is assumed. Secondly, a speed increment
delta v is exerted along a tangential direction so that the
detector sets off from the periodical
orbit near the
dynamic balance points. Based on a multiple-body model, relations between the detector and a distance df of the detector and the target small
celestial body, a flying period tf and the tangential direction speed increment
delta v are built up when the detector flies across the target small
celestial body is built. Through an optimizing
algorithm, an initial value of the
transfer orbit is obtained when the fight distance df is minimum. Finally, a secondary-level
differential correction method is used based on the initial value to obtain orbit parameters which can meet two
point boundary values. The interplanetary transfer orbit design method can achieve rapid design of flight from the periodical orbit which is near the dynamic balance points of the three-
body system to the small celestial body, calculation amount is small and efficiency is high.