/home/connor/projects/thesis/archive/EM_2022-03-29T21:26:22.750/mission---------------------------

Spacecraft: mySat
	dry_mass: 200.0 kg
	specific impulse: 3200.0 kg/s
	max_thrust: 0.00025 kN
	num_thrusters: 1
	duty_cycle: 1.0
Launch Mass: 3500.0 kg
Launch Date: 2024-04-22T09:55:35.770
Launch V∞: [7.3434961975052575, 2.1070520149056207, -1.014351173307538] km/s
Phase 1:
	Planet: Mars
	V∞_in: [-4.0891408313442243e-10, -1.3519558171080589e-9, -2.9347938509608335e-9] km/s
	V∞_out: [-1.009960237699357e-8, -1.009960237699357e-8, 7.767450588932219e-10] km/s
	time of flight: 8.599031774086058e7 seconds
	arrival date: 2027-01-12T16:07:32.770
	thrust profile: [0.10180817450485931 0.010765994728988202 -0.007544294859875064; 0.16235850598372423 0.10642344368168269 -0.0003675622257710981; 0.1012089195326011 0.215498048785662 0.009263152266136488; -0.005263860097698059 0.23018146612119708 0.014653161556634695; -0.07216616837405394 0.1886632498893549 0.01482047592832661; -0.09398125027080778 0.12777759796739516 0.011338047777898999; -0.08181401680555038 0.06911303246065172 0.005833525852290107; -0.046580710304300145 0.02548722787737307 -0.000870777813142698; 0.0008108654501895264 -0.002069527547353827 -0.010201717802848145; 0.034561814232433444 -0.014025534635558886 -0.008973491598575703; 0.08747966934536043 -0.003895559625340753 -0.007112515261902957; 0.15550075175184433 0.018424169433452726 -0.005669922341139337; 0.20248982822207362 0.14526574995002947 0.0013158139705482853; 0.1119856201004996 0.257928321038749 0.011672620538172137; -0.013956968702964088 0.25905748898149866 0.016710191647944732; -0.08713823665180384 0.20616330494298554 0.01620667875500915; -0.10696574449396443 0.13889689572070454 0.012648766692620108; -0.09152920511480982 0.07897071043001104 0.008095327395193714; -0.05734765938030889 0.03602736492249166 0.004000200225081728; -0.018669314030212245 0.009667853783132363 0.0010959107001852323] %

Mass Used: 102.10077631610102 kg
Launch C3: 59.395512899082384 km²/s²
||V∞_in||: 3.256994044580908e-9 km/s