nyx-space 1.0.0-beta.1

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

# This example is taken from Poliastro

[state.iss_init]
x = 8.59072560e2
y = -4.13720368e3
z = 5.29556871e3
vx = 7.37289205
vy = 2.08223573
vz = 4.39999794e-1
frame = "EME2000"
epoch = "2013-03-18T12:00:00.0 UTC"
unit_position = "km"  # Default value if unspecified
unit_velocity = "km/s"  # Default value if unspecified

[orbital_dynamics.iss]
integration_frame = "EME2000"
initial_state = "iss_init"
point_masses = ["Earth"]
accel_models = ["my_models"]

[spacecraft.iss]
dry_mass = 100.0
fuel_mass = 20.0
orbital_dynamics = "iss"

[propagator.iss]
dynamics = "iss"
stop_cond = "30.0 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/iss.csv"
headers = ["epoch:GregorianUtc", "x", "y", "z", "vx", "vy", "vz", "rmag:Luna"]

[propagator.iss_cond]
dynamics = "iss"
stop_cond = "apo"
output = "my_csv"
tolerance = 1e-9

[conditions.apo]
event = "apoapsis"
search_until = "2013-03-18T14:00:00.0 UTC"