issue_plot.py

import matplotlib.pyplot as plt
from astropy import units as u
from astropy.time import Time

from poliastro.bodies import Earth, Mars
from poliastro.maneuver import Maneuver
from poliastro.plotting.static import StaticOrbitPlotter
from poliastro.twobody import Orbit

# Departure and time of flight for the mission
EPOCH_DPT = Time("2018-12-01")
EPOCH_ARR = EPOCH_DPT + 2 * u.year

# Origin and target orbits
ss_earth = Orbit.from_body_ephem(Earth, epoch=EPOCH_DPT)
ss_mars = Orbit.from_body_ephem(Mars, epoch=EPOCH_ARR)

man = Maneuver.lambert(ss_earth, ss_mars, short=False, M=1)
ss_trans, ss_target = ss_earth.apply_maneuver(man, intermediate=True)

op = StaticOrbitPlotter()
op.plot(ss_earth, label="Earth", color="navy")
op.plot(ss_mars, label="Mars", color="darkred")
op.plot(ss_trans, label="Long transfer", color="green")
plt.show()