def PlotEccOrbit_aRs(par,t):
"""Function to plot planet orbit in 3D"""
#read in parameters
T0,P,a_Rstar,p,b,c1,c2,e,w,foot,Tgrad,Sec_depth = par
#ensure b and p >= 0
if b<0.: b=-b
if p<0.: p=-p
w *= np.pi / 180.
i = np.arccos(b/a_Rstar)
#make w lie in range 0-2pi
if w >= 2*np.pi:
w -= 2*np.pi #make f lie in range 0-2pi
elif w < 0:
w += 2*np.pi #make f lie in range 0-2pi
#true anomaly of central transit time
f = 1.*np.pi/2. + w
if f >= 2*np.pi:
f -= 2*np.pi #make f lie in range 0-2pi
elif f < 0:
f += 2*np.pi #make f lie in range 0-2pi
if f < np.pi:
E = np.arccos( (np.cos(f) + e) / (e*np.cos(f)+1.) )
M_tr = E - e*np.sin(E)
T_peri = T0 + M_tr * P/(2*np.pi)
if f >= np.pi:
#f = np.pi - f #correct for acos calc
E = np.arccos( (np.cos(f) + e) / (e*np.cos(f)+1.) )
M_tr = E - e*np.sin(E)
#M_tr = 2*np.pi - M_tr
T_peri = T0 - M_tr * P/(2*np.pi)
#calculate mean anomaly
M = (2*np.pi/P) * (t - T_peri)
#get coords
x = PlanetOrbit.get_x(M,a_Rstar,e,w)
y = PlanetOrbit.get_y(M,a_Rstar,e,w,i)
z = PlanetOrbit.get_z(M,a_Rstar,e,w,i)
#make plot
ax = Axes3D(pylab.gcf())
ax.plot(x, y, z, c='k')
ax.scatter(x, y, z, c='r', s=50)
ax.scatter([0],[0],[0],c='y', s=500) #plot star position
ax.scatter([x[0],],[y[0],],[z[0],],c='g', s=100) #plot initial planet position
ax.scatter([x[1],],[y[1],],[z[1],],c='y', s=100) #plot initial planet position
ax.set_xlabel('X')
ax.set_ylabel('Y')
ax.set_zlabel('Z')
range = abs(np.array([x,y,z])).max()
ax.set_xlim3d(-range,range)
ax.set_ylim3d(-range,range)
ax.set_zlim3d(-range,range)
def PlotEccOrbit(par,t):
"""Function to plot planet orbit in 3D"""
#read in parameters
T0,P,Mstar,Mplanet,Rstar,p,i,c1,c2,e,w,foot,Tgrad,Sec_depth = par
#convert units
Rstar *= Cnst.RSun
Mstar *= Cnst.MSun
Mplanet *= Cnst.MJup
i *= np.pi / 180.
w *= np.pi / 180.
#semi-major axis
a = np.power( ( ((P*24.*60.*60./(2*np.pi))**2 * Cnst.G * (Mstar+Mplanet) ) ) , (1./3.) )
#make w lie in range 0-2pi
if w >= 2*np.pi:
w -= 2*np.pi #make f lie in range 0-2pi
elif w < 0:
w += 2*np.pi #make f lie in range 0-2pi
#true anomaly of central transit time
f = 1.*np.pi/2. + w
if f >= 2*np.pi:
f -= 2*np.pi #make f lie in range 0-2pi
elif f < 0:
f += 2*np.pi #make f lie in range 0-2pi
if f < np.pi:
E = np.arccos( (np.cos(f) + e) / (e*np.cos(f)+1.) )
M_tr = E - e*np.sin(E)
T_peri = T0 + M_tr * P/(2*np.pi)
if f >= np.pi:
#f = np.pi - f #correct for acos calc
E = np.arccos( (np.cos(f) + e) / (e*np.cos(f)+1.) )
M_tr = E - e*np.sin(E)
#M_tr = 2*np.pi - M_tr
T_peri = T0 - M_tr * P/(2*np.pi)
#calculate mean anomaly
M = (2*np.pi/P) * (t - T_peri)
#get coords
x = PlanetOrbit.get_x(M,a/Rstar,e,w)
y = PlanetOrbit.get_y(M,a/Rstar,e,w,i)
z = PlanetOrbit.get_z(M,a/Rstar,e,w,i)
#make plot
ax = Axes3D(pylab.gcf())
ax.plot(x, y, z, c='k')
ax.scatter(x, y, z, c='r', s=50)
ax.scatter([0],[0],[0],c='y', s=500) #plot star position
ax.scatter([x[0],],[y[0],],[z[0],],c='g', s=100) #plot initial planet position
ax.scatter([x[1],],[y[1],],[z[1],],c='y', s=100) #plot initial planet position
ax.set_xlabel('X')
ax.set_ylabel('Y')
ax.set_zlabel('Z')
range = abs(np.array([x,y,z])).max()
ax.set_xlim3d(-range,range)
ax.set_ylim3d(-range,range)
ax.set_zlim3d(-range,range)