23 lines
1.9 KiB
Plaintext
23 lines
1.9 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T21:33:01.420/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: 2023-03-11T16:02:09.080
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Launch V∞: [7.290339628882368, -1.8288440801615886, -6.632030600228825] km/s
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Phase 1:
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Planet: Mars
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V∞_in: [-0.003664456556782759, -0.0036510052522354575, -0.0017682821659383713] km/s
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V∞_out: [-0.1893444115511239, 0.18934441155112372, -0.07646642757306271] km/s
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time of flight: 9.309960005487782e7 seconds
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arrival date: 2026-02-21T05:02:09.080
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thrust profile: [-0.1746457094907778 -0.05324520729862655 0.49134886061939687; -0.627027503294072 -0.40066969942751784 0.5818755748236487; -0.4247709197544459 -0.70455535681447 -0.18137441849457178; 0.39985450427415964 -0.6472758630327436 -0.6430237844213548; 0.4656645028614102 -0.26488366431804417 -0.7314105489598725; 0.1191067639913546 0.2223158565414293 -0.7468478853961351; -0.3933541564722199 0.058176480588614785 -0.7289724142316767; -0.5058338906252844 -0.4156231661282735 -0.5643546902998223; -0.5318185912755031 -0.6386622831457283 0.08080900296257724; 0.27321630774062744 -0.7220941798748955 -0.042143171437234374; 0.5425105272566577 -0.48807460643793443 -0.3531814327468772; 0.3522022888052473 0.06262879123129814 -0.6401364976996247; -0.1561236716305922 0.5164836976614604 -0.7196848157274702; -0.6067507933991897 0.5079757344850814 -0.7392991893046754; -0.7130116758304386 0.10035106755129632 -0.6845824948634448; -0.6878836289874771 -0.5954631055945753 -0.6809457412241607; -0.3269757395259158 -0.7281706083760071 -0.725121591528696; 0.5029082823724691 -0.7211592525685994 -0.6308100968795103; 0.5368458661526178 -0.4216537659711369 -0.14188422812553816; 0.16194407043490938 -0.2071575272584137 0.018329982767622783] %
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Mass Used: 633.2884274220719 kg
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Launch C3: 100.4775524563663 km²/s²
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||V∞_in||: 0.005466708610011581 km/s
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