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{
"name": "SS520",
"output file name": "SS520",
"calculate condition": {
"start time[s]": 0,
"end time[s]": 10000,
"time step[s]": 0.2
},
"launch": {
"position LLH[deg,deg,m]": [31.251808, 131.078999, 267.0],
"velocity NED[m/s]": [0.0, 0.0, 0.0],
"time": [2016,1,1,12,0,0]
},
"1st stage": {
"mass initial[kg]": 2200.0,
"thrust": {
"Isp[s]": 190.0,
"file exist": true,
"file name": "SS520-4-1_thrust.csv",
"const thrust[N]": 25000,
"burn start time[s]": 0.0,
"burn end time[s]": 33.0,
"throat diameter[m]": 0.1768,
"nozzle expansion ratio": 8,
"nozzle exhaust pressure[Pa]": 101300
},
"aero": {
"body diameter[m]": 0.52,
"lift coefficient file exist": false,
"lift coefficient file name": "CL.csv",
"lift coefficient": 0.0,
"drag coefficient file exist": true,
"drag coefficient file name": "SS520-4-1_CD.csv",
"drag coefficient": 0.5
},
"attitude": {
"file exist": true,
"file name": "SS520-4-1_attitude.csv",
"initial elevation[deg]": 75.0,
"initial azimth[deg]": 120
},
"stage": {
"following stage exist": true,
"separation time[s]": 31.7
}
},
"2nd stage": {
"mass initial[kg]": 510.0,
"thrust": {
"Isp[s]": 264.8,
"file exist": true,
"file name": "SS520-4-2_thrust.csv",
"const thrust[N]": 35000,
"burn start time[s]": 138.3,
"burn end time[s]": 161.7,
"throat diameter[m]": 0.1,
"nozzle expansion ratio": 10,
"nozzle exhaust pressure[Pa]": 0
},
"aero": {
"body diameter[m]": 0.1,
"lift coefficient file exist": false,
"lift coefficient file name": "CL.csv",
"lift coefficient": 0.0,
"drag coefficient file exist": false,
"drag coefficient file name": "CD.csv",
"drag coefficient": 0.2
},
"attitude": {
"file exist": false,
"file name": "attitude.csv",
"initial elevation[deg]": 0.0,
"initial azimth[deg]": 99
},
"stage": {
"following stage exist": true,
"separation time[s]": 228
}
},
"3rd stage": {
"mass initial[kg]": 86.0,
"thrust": {
"Isp[s]": 264.8,
"file exist": true,
"file name": "SS520-4-3_thrust.csv",
"const thrust[N]": 8000,
"burn start time[s]": 0.0,
"burn end time[s]": 25.6,
"throat diameter[m]": 0.05,
"nozzle expansion ratio": 10,
"nozzle exhaust pressure[Pa]": 0
},
"aero": {
"body diameter[m]": 0.1,
"lift coefficient file exist": false,
"lift coefficient file name": "CL.csv",
"lift coefficient": 0.0,
"drag coefficient file exist": false,
"drag coefficient file name": "CD.csv",
"drag coefficient": 0.2
},
"attitude": {
"file exist": false,
"file name": "attitude.csv",
"initial elevation[deg]": 0.0,
"initial azimth[deg]": 99
},
"stage": {
"following stage exist": false,
"separation time[s]": 100
}
},
"payload": {
"weight": 1,
"deploy time": 10000
},
"parachute": {
"exist": false,
"drag coefficient": 1.0,
"diameter": 1.5,
"deploy time": 100
},
"wind": {
"file exist": false,
"file name": "wind.csv",
"const wind": [0.0, 0.0]
}
}