A Shape-Based Method for Continuous Low-Thrust Trajectory Design between Circular Coplanar Orbits

Table 2

Simulation results using different initial guesses in the Earth-Mars case.

	before optimization	after optimization	Optimization time
OFS method	0.1896 DU/TU	0.18787 DU/TU	12.029 s
TFS method	0.2514 DU/TU	0.18908 DU/TU	10.943 s
Hohmann	0.1877 DU/TU