Abstract:

Transfer trajectory design with the orbit insertion point on the stable manifold of the Halo orbit was studied. First, the mathematical model was given, and the Halo orbit and the corresponding stable manifold were computed. Then, the design method of the transfer trajectory was briefly introduced. Finally, the stable manifold with minimal Earth distance was taken as the nominal stable manifold; the transfer trajectory with insertion point on different positions of the stable manifold was computed using differential correction; the effects of manifold insertion point on the insertion maneuvering velocity and on the flight time of the transfer trajectory were analyzed. Numerical simulation shows that there are three local minimal points of the insertion maneuvering velocity. If the manifold insertion point is selected in the vicinity of the second minimal point, the insertion maneuvering velocity saves 10 m/s than that of ISEE3 while the flight time remains the same.

Key words: control and navigation technology of aerocraft, Halo orbit, transfer trajectory, invariant manifold, manifold insertion