Low-Thrust Trajectory Design Using Finite Fourier Series Approximation of Pseudoequinoctial Elements

Table 5

Comparison of the asteroid 1989ML rendezvous mission by different methods.

No.	(km/s)	(m/s^2)	(N)
PE-FFS	4.58	3.1	0.30
3D-FFS [31]	4.20	3.1	0.30
GPOPS [31]	4.02	—	0.30
Indirect [31]	4.02	—	0.30
Spherical [20]	4.47	—	0.31
PE [20]	4.82	—	0.33
Hodographic [22]	4.22	4.7	—