23 lines
2.0 KiB
Plaintext
23 lines
2.0 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T21:44:52.679/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: 2024-01-22T12:08:19.865
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Launch V∞: [9.999999510580688, -9.997198712980596, 0.2367016801977378] km/s
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Phase 1:
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Planet: Mars
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V∞_in: [-0.000819918545143649, -0.0012451509155042646, -0.001250921976389137] km/s
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V∞_out: [0.0019338785602035886, -0.0019338785602035886, -0.0006601321083539838] km/s
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time of flight: 1.7233962915051136e7 seconds
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arrival date: 2024-08-08T23:21:01.865
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thrust profile: [-2.3909756762714905e-7 3.7137254328500285e-7 6.84557970113123e-10; -6.490849187612506e-7 -1.6923622503113822e-7 7.597297006308147e-8; -1.3462011970258392e-7 5.4785730096847575e-8 3.065595287593101e-8; 0.15976947743667638 -0.2920794439050224 0.002394761620150665; 0.5616910709675398 -0.7901992734350411 0.010726222487855458; 1.0 -1.0 -0.0032456678933753843; 1.0 -0.6953371235997132 -0.00807847832727659; 1.0 -0.23068593990468247 -0.009476805297354552; 1.0 0.06616898317798338 -0.009396139547492788; 0.8458292750604345 0.20752997653151717 -0.009416373557718996; 0.4899942520164369 0.18998472141046954 -0.007666776709170746; 0.03957676169176063 0.0210088124260986 -0.0012531497610165998; -5.452577185178014e-7 -3.4799035186607614e-7 -1.0511021967736704e-7; -1.3251613739747719e-8 3.0514099445579054e-7 4.002333800730656e-8; 1.6516923938790852e-8 -9.029916507496571e-8 8.144270988392475e-8; 6.025616118742147e-7 -5.477234118696148e-7 1.5445834673209101e-6; 1.2522336398625811e-7 -1.1634639614565971e-6 3.2890058545783734e-7; -1.8707392087284995e-7 1.037143716480063e-7 2.3487962795435016e-7; -1.0032847526436222e-6 -9.961208338104671e-7 1.0945507651240803e-6; 1.5694593639258316e-6 -4.2952948369892885e-7 -3.8494467904625947e-7] %
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Mass Used: 50.813640071233294 kg
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Launch C3: 200.0000000038433 km²/s²
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||V∞_in||: 0.0019461431124315834 km/s
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