23 lines
2.0 KiB
Plaintext
23 lines
2.0 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T22:58:44.883/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: 2023-04-14T07:05:59.170
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Launch V∞: [1.6949045581275466, -1.1749158457323354, 0.4459844940604056] km/s
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Phase 1:
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Planet: Mars
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V∞_in: [0.2807404173223861, -0.5148397948760617, -0.024574238754993954] km/s
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V∞_out: [0.4816521199334624, -0.31105824990728403, 0.021223537272540942] km/s
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time of flight: 1.0181159999765144e8 seconds
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arrival date: 2026-07-05T16:05:58.170
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thrust profile: [1.4156868146913603e-5 -8.937824771836181e-6 -1.4258721529256393e-6; 6.201501805968712e-6 4.891054084739865e-6 -2.4147768084891413e-5; 8.710377800639082e-6 -2.5247715656786118e-5 -4.228464809233087e-5; -5.49592858423698e-6 -5.956986519709633e-6 -6.0003598197038516e-6; -2.2049093171105036e-6 -2.489010425867444e-6 -3.9225913222362265e-6; 2.1078914306123458e-5 -1.1944173566312533e-5 1.8244198561717057e-5; 1.9561991087389005e-6 -1.1752657963774734e-5 1.683487450213938e-5; -6.055159240369156e-6 -2.206637657527475e-5 1.5277910735365964e-5; -2.1063568637137504e-5 1.0199794653949234e-5 -1.0165697723410959e-5; 0.0006945866286583284 -4.8718537131140276e-5 -0.0010004798714153944; 3.549819219472579e-6 -5.173787731590263e-6 -8.794510883495692e-6; -1.1187037009877784e-5 3.9873466996776687e-7 -1.2842230899218392e-5; 1.819371322436169e-5 -1.985114604615626e-5 7.40305445774715e-6; 4.351771410931808e-6 -1.2633771406394241e-5 4.02517242765969e-5; -0.00021811083392391314 -0.006360908650050679 0.007451776526230452; 0.4683451802604527 -0.7651039839559246 0.09069086407503833; 0.8713044694433868 -0.27831401933737787 -0.20462753606922815; 0.012344351227493076 0.0030669853424402133 -0.014728214668807213; 6.768683876914276e-6 7.65498676530381e-6 -2.3634699931764597e-5; 5.463932969042515e-8 1.6589754704890928e-6 -6.114493334584618e-6] %
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Mass Used: 75.80031539540141 kg
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Launch C3: 4.452030874656779 km²/s²
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||V∞_in||: 0.5869234102647126 km/s
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