def orbit2():
planets = [
Planet(1817514095, 1905216634, -1485460920),
Planet(1817514095, 1905216634, -1722015868),
Planet(1817514095, 1905216634, -455609026),
Planet(1817514095, 1905216634, 272811578),
Planet(1817514095, 1905216634, -393577255),
Planet(1817514095, 1905216634, -1420756477),
Planet(1817514095, 1905216634, -93488736),
Star(1817514095, -1385166447, Star(1817514095, 1905216634))
]
t0 = epoch_from_string(str(datetime.now()))
x_val = list()
y_val = list()
z_val = list()
planet_positions = list()
planet_names = list()
planet_colors = list()
for orbiter in planets:
orbit_period = orbiter.planet.compute_period(epoch(0)) * SEC2DAY
orbit_when = np.linspace(0, orbit_period, 60)
x = np.zeros(60)
y = np.zeros(60)
z = np.zeros(60)
for i, day in enumerate(orbit_when):
r, _ = orbiter.planet.eph(epoch(t0.mjd2000 + day))
x[i] = r[0] / AU
y[i] = r[1] / AU
z[i] = r[2] / AU
x_val.append(x.tolist())
y_val.append(y.tolist())
z_val.append(z.tolist())
planet_positions.append(list((x[0], y[0], z[0])))
if orbiter.id == -455609026:
planet_colors.append("green")
else:
planet_colors.append("gray")
planet_names.append(orbiter.name)
return jsonify(success=True,
x=x_val,
y=y_val,
z=z_val,
p=planet_positions,
c=planet_colors,
n=planet_names) if has_app_context() else x_val
def convert_to_epoch(day, month, year):
""" returns epoch for day month and year """
day = str(day)
month = str(month)
year = str(year)
if len(day) < 2:
day = "0" + day
if len(month) < 2:
month = "0" + month
return pk.epoch_from_string(year + '-' + month + '-' + day + ' 23:59:54.003')
seq = [pk.planet.jpl_lp('earth'),pk.planet.jpl_lp('mars')]
print (seq)
# Position des planètes et orbites
# In[69]:
from mpl_toolkits.mplot3d import Axes3D
import matplotlib.pyplot as plt
fig = plt.figure()
ax = fig.gca(projection='3d')
e = pk.epoch_from_string('2019-07-27 17:09:54') #date du jour
pk.orbit_plots.plot_planet(seq[0], e, color = 'b', legend=True, ax=ax)
pk.orbit_plots.plot_planet(seq[1], e, color = 'r', legend=True, ax=ax)
plt.show()
# Launch windonws, time of flight and departure vinf
# In[70]:
#comment sont choisis ces limites ?
t0 = [e,pk.epoch(10000)]
#t0 = [epoch(4000),epoch(10000)]
tof = [60,380]
vinf = [0,4] #fonction du launcher
import matplotlib as mpl
import matplotlib.pyplot as plt
from mpl_toolkits.mplot3d import Axes3D
from pykep import epoch, epoch_from_string, planet, AU, MU_SUN, DEG2RAD
from pykep.planet import jpl_lp, keplerian
from pykep.orbit_plots import plot_planet
mpl.rcParams['legend.fontsize'] = 10
# asteroid @ Epoch 2014-Dec-09 (JD 2,457,000.5)
ast_time = epoch_from_string('2014-12-09 00:00:00.000') #epoch(6800,"mjd2000")
ast_orbel = (2.77 * AU, 0.075, 9.65 * DEG2RAD, 80.33 * DEG2RAD,
72.52 * DEG2RAD, 95.99 * DEG2RAD) # a,e,i,W,w,M (SI and RAD)
ast_mu = 6e10
ast_radius = 1e5
ast_name = 'asteroid'
asteroid = keplerian(ast_time, ast_orbel, MU_SUN, ast_mu, ast_radius,
ast_radius * 1.1, ast_name)
rA, vA = asteroid.eph(ast_time)
#earth
pl = jpl_lp('earth')
rE, vE = pl.eph(ast_time)
# plot
fig = plt.figure()
axis = fig.gca(projection='3d')
axis.scatter([0], [0], [0], color='y') #sun
plot_planet(asteroid,
t0=ast_time,
def transfer():
star = Star(1817514095, 1905216634)
origin = Planet(1817514095, 1905216634, -455609026)
target = Planet(1817514095, 1905216634, 272811578)
origin_orbit_radius = origin.planet.radius + 200000
target_orbit_radius = target.planet.radius + 200000
launch_time_start = int(float(flask_request.values['launch_start']))
launch_time_end = int(float(flask_request.values['launch_end']))
launch_time_offset = 0 if launch_time_start >= 0 else -launch_time_start
flight_time_start = int(float(flask_request.values['flight_start']))
flight_time_start = max(1, flight_time_start)
flight_time_end = int(float(flask_request.values['flight_end']))
flight_time_end = max(1, flight_time_end)
t0 = epoch_from_string(str(datetime.now()))
t0_number = int(t0.mjd2000)
delta_v = np.full((flight_time_end - flight_time_start,
launch_time_end + launch_time_offset), None)
for launch_time in range(launch_time_start, launch_time_end):
for flight_time in range(flight_time_start, flight_time_end):
launch_time = int(launch_time)
launch_time_index = launch_time + launch_time_offset
flight_time = int(flight_time)
flight_time_index = flight_time - flight_time_start
t1 = epoch(launch_time + t0_number)
t2 = epoch(launch_time + t0_number + flight_time)
dt = (t2.mjd - t1.mjd) * DAY2SEC
r1, v1 = origin.planet.eph(t1)
r2, v2 = target.planet.eph(t2)
lambert = lambert_problem(list(r1), list(r2), dt, star.gm)
delta_vs = list()
for x in range(lambert.get_Nmax() + 1):
vp_vec = np.array(v1)
vs_vec = np.array(lambert.get_v1()[x])
vsp_vec = vs_vec - vp_vec
vsp = np.linalg.norm(vsp_vec)
vo = sqrt(vsp * vsp +
2 * origin.planet.mu_self / origin_orbit_radius)
inj_delta_v = vo - sqrt(
origin.planet.mu_self / origin_orbit_radius)
vp_vec = np.array(v2)
vs_vec = np.array(lambert.get_v2()[x])
vsp_vec = vs_vec - vp_vec
vsp = np.linalg.norm(vsp_vec)
vo = sqrt(vsp * vsp +
2 * target.planet.mu_self / target_orbit_radius)
ins_delta_v = vo - sqrt(
target.planet.mu_self / target_orbit_radius)
delta_vs.append(inj_delta_v + ins_delta_v)
delta_v[flight_time_index, launch_time_index] = min(delta_vs)
return jsonify(success=True,
delta_v=delta_v.tolist(),
launch_start=launch_time_start,
launch_end=launch_time_end,
flight_start=flight_time_start,
flight_end=flight_time_end,
launch_offset=-launch_time_offset)
def plottransfer():
star = Star(1817514095, 1905216634)
origin = Planet(1817514095, 1905216634, -455609026)
target = Planet(1817514095, 1905216634, 272811578)
origin_orbit_radius = origin.planet.radius + 200000
target_orbit_radius = target.planet.radius + 200000
flight_time = int(flask_request.values['flight_time'])
t0 = epoch_from_string(str(datetime.now()))
t0_number = int(t0.mjd2000)
launch_time = int(flask_request.values['launch_time']) + t0_number
t1 = epoch(int(launch_time))
t2 = epoch(int(launch_time) + int(flight_time))
fig = plt.figure(figsize=(4, 4))
orbit_ax = fig.gca(projection='3d', proj_type='ortho')
orbit_ax.scatter([0], [0], [0], color='orange')
orbit_ax.set_aspect('equal')
x_fig = plt.figure(figsize=(4, 4))
x_ax = x_fig.gca()
x_ax.scatter([0], [0], color='orange')
y_fig = plt.figure(figsize=(4, 4))
y_ax = y_fig.gca()
y_ax.scatter([0], [0], color='orange')
z_fig = plt.figure(figsize=(4, 4))
z_ax = z_fig.gca()
z_ax.scatter([0], [0], color='orange')
plot_planet(origin.planet,
t0=t1,
color='green',
legend=True,
units=AU,
ax=orbit_ax)
plot_planet(target.planet,
t0=t2,
color='gray',
legend=True,
units=AU,
ax=orbit_ax)
o_x, o_y, o_z = plot_planet_2d(origin.planet, t0=t1)
t_x, t_y, t_z = plot_planet_2d(target.planet, t0=t2)
x_ax.plot(o_y, o_z, label=origin.planet.name, c='green')
x_ax.scatter(o_y[0], o_z[0], s=40, color='green')
x_ax.plot(t_y, t_z, label=target.planet.name, c='gray')
x_ax.scatter(t_y[0], t_z[0], s=40, color='gray')
y_ax.plot(o_x, o_z, label=origin.planet.name, c='green')
y_ax.scatter(o_x[0], o_z[0], s=40, color='green')
y_ax.plot(t_x, t_z, label=target.planet.name, c='gray')
y_ax.scatter(t_x[0], t_z[0], s=40, color='gray')
z_ax.plot(o_x, o_y, label=origin.planet.name, c='green')
z_ax.scatter(o_x[0], o_y[0], s=40, color='green')
z_ax.plot(t_x, t_y, label=target.planet.name, c='gray')
z_ax.scatter(t_x[0], t_y[0], s=40, color='gray')
max_value = max(max([abs(x) for x in orbit_ax.get_xlim()]),
max([abs(x) for x in orbit_ax.get_ylim()]))
max_z_value = max([abs(z) for z in orbit_ax.get_zlim()])
dt = (t2.mjd - t1.mjd) * DAY2SEC
r1, v1 = origin.planet.eph(t1)
r2, v2 = target.planet.eph(t2)
lambert = lambert_problem(list(r1), list(r2), dt, star.gm)
min_n = None
min_delta_v = None
for x in range(lambert.get_Nmax() + 1):
vp_vec = np.array(v1)
vs_vec = np.array(lambert.get_v1()[x])
vsp_vec = vs_vec - vp_vec
vsp = np.linalg.norm(vsp_vec)
vo = sqrt(vsp * vsp + 2 * origin.planet.mu_self / origin_orbit_radius)
inj_delta_v = vo - sqrt(origin.planet.mu_self / origin_orbit_radius)
vp_vec = np.array(v2)
vs_vec = np.array(lambert.get_v2()[x])
vsp_vec = vs_vec - vp_vec
vsp = np.linalg.norm(vsp_vec)
vo = sqrt(vsp * vsp + 2 * target.planet.mu_self / target_orbit_radius)
ins_delta_v = vo - sqrt(target.planet.mu_self / target_orbit_radius)
if min_delta_v is None or inj_delta_v + ins_delta_v < min_delta_v:
min_n = x
min_delta_v = inj_delta_v + ins_delta_v
plot_lambert(lambert,
color='purple',
sol=min_n,
legend=False,
units=AU,
ax=orbit_ax)
l_x, l_y, l_z = plot_lambert_2d(lambert, sol=min_n)
x_ax.plot(l_y, l_z, c='purple')
y_ax.plot(l_x, l_z, c='purple')
z_ax.plot(l_x, l_y, c='purple')
orbit_ax.set_xlim(-max_value * 1.2, max_value * 1.2)
orbit_ax.set_ylim(-max_value * 1.2, max_value * 1.2)
orbit_ax.set_zlim(-max_z_value * 1.2, max_z_value * 1.2)
x_ax.set_xlim(-1.0, 1.0)
x_ax.set_ylim(-0.05, 0.05)
y_ax.set_xlim(-1.0, 1.0)
y_ax.set_ylim(-0.05, 0.05)
z_ax.set_xlim(-1.0, 1.0)
z_ax.set_ylim(-1.0, 1.0)
fig.savefig('orbit')
x_fig.savefig('orbit-x')
y_fig.savefig('orbit-y')
z_fig.savefig('orbit-z')
plt.close('all')
return jsonify(success=True)