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%matplotlib inline
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from numpy import radians
from scipy.constants import kilo
from orbital import earth, KeplerianElements, Maneuver, plot, plot3d
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# Create molniya orbit from period and eccentricity
from orbital import earth_sidereal_day
molniya = KeplerianElements.with_period(
earth_sidereal_day / 2, e=0.741, i=radians(63.4), arg_pe=radians(270),
body=earth)
# Simple circular orbit
orbit = KeplerianElements.with_altitude(1000 * kilo, body=earth)
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plot(molniya)
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plot3d(molniya)
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plot(molniya, title='Molniya 1', animate=True);
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plot3d(molniya, title='Molniya 2', animate=True);
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man = Maneuver.hohmann_transfer_to_altitude(10000 * kilo)
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plot(orbit, title='Maneuver 1', maneuver=man)
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plot3d(orbit, title='Maneuver 2', maneuver=man)