23 lines
2.1 KiB
Plaintext
23 lines
2.1 KiB
Plaintext
/home/connor/projects/thesis/archive/EM_2022-03-29T22:59:31.051/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: 2023-12-23T04:52:28.411
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Launch V∞: [-2.3721677208600336, -1.1471540814232561, 1.82724714241875] km/s
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Phase 1:
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Planet: Mars
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V∞_in: [0.7657978493736273, 0.47268498190867225, 0.5669638080447448] km/s
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V∞_out: [0.671344291602754, 0.7165876747149759, 0.4086328277033566] km/s
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time of flight: 6.692110088878082e7 seconds
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arrival date: 2026-02-04T18:04:08.411
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thrust profile: [0.0008233730574660627 -0.0006089913686355275 -0.0003656792494954692; 9.277035119329392e-5 0.00018105994933842137 -0.00045064421020144603; -0.0009643656591043792 -0.0005295771327107068 -0.0003527133652685661; -0.0001829291084087302 -0.00028713103539127654 -0.0011612339233188311; 0.0002628094997902115 -0.00038049047451517036 -0.0004438420586700227; 0.00022847673868341134 -8.081668903608331e-5 -0.0004169573293423967; -0.00024469370633056417 -6.337239455279198e-5 0.0008380473882381952; 0.0007752101556583943 0.0006834443935228009 0.00015265143847038387; -5.4459788825500716e-5 -0.0014820986794018846 -0.0012653925633815618; -0.00021218967607504187 -0.00020847681093790597 -0.0002734855651715473; -0.00017082953277056904 -0.00011256508693154773 0.00152134489853549; -0.0007743596333968497 8.88770635961271e-5 0.001957585876424173; -0.0009465135793430943 -0.0008606487267644376 -0.000381605440474747; -0.002413182432020938 -0.0026073704810047824 -0.00027904268175806847; -0.0005254492375900773 -0.002157747734677348 -0.001799801241758866; -0.0005194698886906513 -0.001005331073405558 -0.0013843897937889358; 0.00048689741373146193 -0.001401700406807511 -0.0024375166130219906; 7.266464024313168e-5 -0.00033741672866423523 -0.0004478141428623512; -0.000586239166722991 0.00012793840622519977 -0.0009074360302595961; -0.00018809051058659194 9.565179941071708e-6 0.000633927457634841] %
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Mass Used: 0.7381269704351325 kg
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Launch C3: 10.281974301893808 km²/s²
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||V∞_in||: 1.0636378132897837 km/s
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