nyx-space 0.0.21

A high-fidelity space mission toolkit, with orbit propagation, estimation and some systems engineering
Documentation 
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sequence = ["prop_km", "prop_m", "prop_cm"]

[state.state_name]
x = -2436.45
y = -2436.45
z = 6891.037
vx = 5.088611
vy = -5.088611
vz = 0.0
frame = "EME2000"
epoch = "MJD 51544.5 TAI" # or "2018-09-15T00:15:53.098 UTC"
unit_position = "km"  # Default value if unspecified
unit_velocity = "km/s"  # Default value if unspecified

[state.state_m]
x = -2436450.0
y = -2436450.0
z = 6891037.0
vx = 5088.611
vy = -5088.611
vz = 0.0
frame = "EME2000"
epoch = "MJD 51544.5 TAI" # or "2018-09-15T00:15:53.098 UTC"
unit_position = "m"  # Default value if unspecified
unit_velocity = "m/s"  # Default value if unspecified

[state.state_cm]
x = -243645000.0
y = -243645000.0
z = 689103700.0
vx = 508861.1
vy = -508861.1
vz = 0.0
frame = "EME2000"
epoch = "MJD 51544.5 TAI" # or "2018-09-15T00:15:53.098 UTC"
unit_position = "cm"  # Default value if unspecified
unit_velocity = "cm/s"  # Default value if unspecified

[orbital_dynamics.conf_name]
integration_frame = "EME2000"
initial_state = "state_name"
point_masses = ["Sun", "Earth", "Jupiter", "Luna"]
accel_models = ["my_models"]

[orbital_dynamics.conf_m]
integration_frame = "EME2000"
initial_state = "state_m"
point_masses = ["Sun", "Earth", "Jupiter", "Luna"]
accel_models = ["my_models"]

[orbital_dynamics.conf_cm]
integration_frame = "EME2000"
initial_state = "state_m"
point_masses = ["Sun", "Earth", "Jupiter", "Luna"]
accel_models = ["my_models"]

[spacecraft.sc1]
dry_mass = 100.0
fuel_mass = 20.0
orbital_dynamics = "conf_name"

[propagator.prop_km]
dynamics = "sc1"
stop_cond = "3.5 days"
output = "my_csv"

[accel_models.my_models.harmonics.jgm3_70x70]
frame = "EME2000"
degree = 70
order = 70
file = "data/JGM3.cof.gz"

[output.my_csv]
filename = "./data/scenario-run.csv"
headers = ["epoch:GregorianUtc", "x", "y", "z", "vx", "vy", "vz", "rmag:Luna"]

[spacecraft.sc1_m]
dry_mass = 100.0
fuel_mass = 20.0
orbital_dynamics = "conf_m"

[spacecraft.sc1_cm]
dry_mass = 100.0
fuel_mass = 20.0
orbital_dynamics = "conf_cm"

[propagator.prop_m]
dynamics = "sc1_m"
stop_cond = "3.5 days"
output = "my_csv_m"

[propagator.prop_cm]
dynamics = "sc1_cm"
stop_cond = "3.5 days"
output = "my_csv_cm"

[output.my_csv_m]
filename = "./data/scenario-run-m.csv"
headers = ["epoch:GregorianUtc", "x", "y", "z", "vx", "vy", "vz", "rmag:Luna"]

[output.my_csv_cm]
filename = "./data/scenario-run-cm.csv"
headers = ["epoch:GregorianUtc", "x", "y", "z", "vx", "vy", "vz", "rmag:Luna"]