Autonomous Planning of Multigravity-Assist Trajectories with Deep Space Maneuvers Using a Differential Evolution Approach

Table 8

Optimal trajectory of Earth-Jupiter mission (EVEEJ) using HGDE.

Mission parameter	Zero-DSM model	MGADSM model
Planet sequence	EVEEJ	EVEEJ
Departure date	01-Mars-2018 11:53:57	26-Feb-2018 06:08:00
Departure impulse (km/s)	3.4952	2.887
DSM date	—	10-Dec-2018 08:40:45
DSM impulse (km/s)	—	0.38609
Venus swing-by date	10-Apr-2019 11:51:46	01-Apr-2019 05:27:15
Postswing-by impulse (km/s)	0.0	0.0
Earth swing-by date	20-Oct-2021 03:45:19	19-Oct-2021 18:56:15
Post-swing-by impulse (km/s)	0.0	0.0
Earth swing-by date	19-Jun-2023 19:03:28	18-Jun-2023 23:16:31
Post-swing-by impulse (km/s)	0.0	0.0
Arrival date	01-Mar-2026 16:05:27	16-Feb-2026 06:58:55
Arrival impulse (km/s)	5.688	5.693
Time of flight (days)	404.99-923.66-607.64-985.88	399-932.6-607.2-973.3
Mission cost (km/s)	9.19	8.97