23 lines
2.1 KiB
Plaintext
23 lines
2.1 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T22:26:29.640/mission---------------------------
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Spacecraft: mySat
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dry_mass: 200.0 kg
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specific impulse: 3200.0 kg/s
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max_thrust: 0.00025 kN
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num_thrusters: 1
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duty_cycle: 1.0
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Launch Mass: 3500.0 kg
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Launch Date: 2024-05-10T14:47:37.584
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Launch V∞: [8.454590640928295, 9.260765024912534, -0.9885318724952183] km/s
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Phase 1:
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Planet: Mars
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V∞_in: [-0.006319696103929528, -0.0412349395695302, 0.025407019305862494] km/s
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V∞_out: [0.022415695471427622, -0.032554221329412304, 0.028687979305271248] km/s
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time of flight: 1.8230010689416587e7 seconds
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arrival date: 2024-12-07T14:41:07.584
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thrust profile: [-0.0002622529733463554 0.00010449975350988813 -0.00012030102951252053; 2.2564340820408038e-5 -3.981832926552484e-5 -7.923191359546866e-6; 5.169422416636556e-5 -5.810036687510864e-5 0.00011428268526115506; -0.00014971921355914664 -0.00014100200005065646 0.00016890254129742059; 0.00015620328410727985 -3.366292385390309e-5 -0.00020340087014733029; -3.210609078978168e-5 -6.498562052193143e-5 5.338807325839352e-5; -8.516237377437068e-5 -0.0001612296252470605 4.209812632127493e-6; 6.305171484191589e-5 -0.001682367723787057 3.8599641512170114e-5; 2.2345674659450702e-5 6.798172919803859e-5 -0.0001184406426706027; -1.6251278244512348e-5 -6.533351590187232e-5 -3.92438433311786e-6; -0.00036512149400096404 -4.6068321314717516e-5 -5.609213629078427e-5; -5.621377289755845e-5 2.1241246976381148e-5 -3.414115489177037e-5; -0.00034119461694600184 -6.972852980194507e-5 2.2003699273903694e-5; 0.00018976563510694219 -9.050300294247073e-6 0.00012300348192681063; 5.426150865573059e-5 -0.00010044444909460297 4.785290273646994e-5; -4.4309429079208605e-5 7.02628779669344e-5 -4.7916743218706474e-5; -8.408538773370183e-5 -4.412949196949812e-5 2.4492265814848663e-5; 0.00011172380033234707 6.642438716286984e-5 9.399896039444412e-6; 8.401331768830077e-6 4.877367093015932e-6 -1.2408399381198787e-6; 9.503407085636648e-5 -0.0002551562074474474 -1.3659784774574114e-5] %
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Mass Used: 0.03575572314321107 kg
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Launch C3: 158.21906701525444 km²/s²
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||V∞_in||: 0.0488444001924202 km/s
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