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

Table 2

Bounds of Earth-Mars mission's design variables using HGGA.

Design variables	Lower bound	Upper bound
No. of swing-by maneuvers	0	2
Swing-by planets	2 (Venus)	3 (Earth)
No. of DSMs per leg	0	2
Flight direction, 𝑓	Prograde	Retrograde
Departure date, 𝑡𝑑	01-Jun-2004	01-December-2004
Arrival date, 𝑡𝑎	01-Apr-2005	01-July-2005
Time of flight (days)/leg, 𝑇1,…,𝑇𝑖	40	300
Swing-by normalized pericenter altitude, ℎ1,…,ℎ𝑖	0.8	5
Swing-by plane rotation angle (rad), 𝜂1,…,𝜂𝑖	0	2𝜋
Epoch of DSM, 𝜀1,…,𝜀𝑗	0.1	0.9
DSM (km/s), Δ𝑣1,…,Δ𝑣𝑘	−5	5