23 lines
2.1 KiB
Plaintext
23 lines
2.1 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T22:35:03.801/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: 2024-10-15T00:59:25.735
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Launch V∞: [0.08411754828864794, 3.867780292357817, 2.507975455218117] km/s
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Phase 1:
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Planet: Mars
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V∞_in: [-0.01111567461793714, -0.2019526290080634, -0.10099494494608693] km/s
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V∞_out: [0.05863131293194478, -0.1437072200747788, -0.16341819092150492] km/s
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time of flight: 2.122969403809613e7 seconds
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arrival date: 2025-06-17T18:07:39.735
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thrust profile: [-0.0019253353195135495 -0.006208595765491277 -0.0030413706831210283; -0.005094954059343889 -0.006884862652799308 -0.007716049803660748; -0.001169679362784149 -0.003040509785898553 -0.0023827736029818115; -0.0009800602675577555 -0.005005973318342694 -0.0007235675342944551; -0.0035541375195941027 -0.0010759580832810519 -0.0011368932928665326; -0.004023727803229634 -0.0024144419030426778 -0.0020601786180336804; -0.009415901341030907 -0.007648304620004416 0.008910953721132594; 0.00019160911662570728 -0.00041311185476429913 0.002747155966524439; -0.0005053512629044138 -0.000435305465528584 0.0010810134121178056; 0.0018400336528207576 -0.006748721129952468 0.002259933413232509; 0.00022745932395296879 0.010666778341568943 0.0035537786550811704; -0.0004423321131218159 -4.1278833244748e-6 0.0012966352168264361; 0.00584099379819922 0.010506361039734275 0.0023162665551785394; -0.0013489272396317838 -0.0016553055603146898 0.00247736021958195; -0.0003060718810677023 0.0030689000185227426 -0.00026453391075189313; -0.004902002300222478 -0.006091743775746333 -0.0007723370782334376; -0.0010727586684161662 -0.0015117821322166705 -0.0011100152254532457; 0.001981284413785558 0.002082711629710382 0.000757647029883398; 0.0002652136199514425 -0.004511943969868106 0.0007431379304516129; 0.0007883244474613861 -0.00476964812130089 3.034140598992801e-5] %
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Mass Used: 0.9889560483511559 kg
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Launch C3: 21.256741035858134 km²/s²
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||V∞_in||: 0.22607167334751047 km/s
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