23 lines
1.6 KiB
Plaintext
23 lines
1.6 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T22:11:59.808/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: 2024-07-12T14:57:14.038
|
|
Launch V∞: [-2.1356055281697612, 10.0, -9.769298185542464] km/s
|
|
Phase 1:
|
|
Planet: Mars
|
|
V∞_in: [-1.4198898735875047, 1.3740951409636546, -1.4192321863480188] km/s
|
|
V∞_out: [1.4110404995307853, -2.1212048062899553, -0.6728408923695377] km/s
|
|
time of flight: 1.5440221824979678e7 seconds
|
|
arrival date: 2025-01-07T07:54:15.038
|
|
thrust profile: [0.05956977091681903 1.0 -0.10922677780373319; 0.23817833345981507 1.0 0.09826946570814477; 0.40293966085543176 1.0 0.3551237041998419; 0.5317072540959735 1.0 0.7307023601163831; 0.5078043727484851 1.0 0.9982992529843099; 0.33655425425041224 1.0 1.0; 0.1360349738666649 1.0 1.0; -0.026672364591518467 1.0 1.0; -0.19610649486002443 1.0 1.0; -0.29528444695253986 1.0 1.0; -0.35123463549962813 1.0 1.0; -0.3634631832054668 1.0 1.0; -0.34243556937322644 1.0 1.0; -0.2988969593988343 1.0 1.0; -0.23211645533604322 0.8701239790258618 1.0; -0.13699199073043578 0.48199643592034935 0.6802560133378645; -4.9400538315483375e-8 1.4543622135653008e-7 2.2274035599587473e-7; -2.6590282235167093e-8 6.069199505306199e-8 7.406086114073912e-8; 7.262188061710368e-8 -2.6660015831706114e-8 -1.054025466018286e-8; 7.299781920337516e-9 5.276251956583804e-9 -2.5519508317922344e-8] %
|
|
|
|
Mass Used: 130.30806476829775 kg
|
|
Launch C3: 199.99999800999254 km²/s²
|
|
||V∞_in||: 2.432785380649605 km/s
|