tle_data = [tle_data[i:i+3] for i in range(0, len(tle_data), 3)]
return tle_data
if __name__ == "__main__":
cb = init_central_body()
sphere_coords = cb.plot_attributes()
tle_data = get_tle_data("data/starlink.txt")
count = 1
for tle in tle_data:
print("....Calculating State Vectors for Starlink No. " + str(count) + "....")
# create satellite object and propagate it using orbital elements
sat1 = Satellite(sat_id=1, name="ISS", center_body=cb, sat_type="Communication")
sat1r0, sat1v0 = sat1.propagate_with_tle(tle)
dt = sat1.period/190.0
sat1r0 = sat1r0.tolist()
sat1v0 = sat1v0.tolist()
propagtor1 = op(sat1r0, sat1v0, sat1.period, dt=dt, central_body=cb)
propagtor1.propagate()
propagtor1.rs = propagtor1.rs * 1/6378
if count == 1:
coords = propagtor1.rs
else:
coords = np.concatenate((coords, propagtor1.rs), axis=1)
count= count + 1
print(" ")
print("....Creating final_coords list for writing location data to Blender's Particle Cache....")
a = cb.radius + (iss['perigee height'] + iss['apogee height']) / 2
eles = [
a, iss['e'], iss['i'], iss['raan'], iss['arg_perigee'],
iss['ma@epoch'], iss['Epoch']
]
period = (24.0 * 3600.0) / iss['revs/day']
return eles, period
if __name__ == "__main__":
cb = init_central_body()
sphere_coords = cb.plot_attributes()
# create satellite object and propagate it using orbital elements
sat1 = Satellite(sat_id=1, name="ISS", center_body=cb, sat_type="Station")
sat1r0, sat1v0 = sat1.propagate_with_tle("data/iss.tle")
sat1r0 = sat1r0.tolist()
sat1v0 = sat1v0.tolist()
propagtor1 = op(sat1r0, sat1v0, sat1.period, dt=100.0, central_body=cb)
propagtor1.propagate()
sat2 = Satellite(sat_id=2,
name="Starlink-31",
center_body=cb,
sat_type="Communication")
sat2r0, sat2v0 = sat2.propagate_with_tle("data/starlink-31.tle")
sat2r0 = sat2r0.tolist()
sat2v0 = sat2v0.tolist()
propagtor2 = op(sat2r0, sat2v0, sat2.period, dt=100.0, central_body=cb)
propagtor2.propagate()
