def test_secondary_eclipse():
u1 = np.array([0.3, 0.2])
lc1 = LimbDarkLightCurve(u1)
u2 = np.array([0.4, 0.1])
lc2 = LimbDarkLightCurve(u1)
s = 0.3
ror = 0.08
f = ror**2 * s
lc = SecondaryEclipseLightCurve(u1, u2, s)
t = np.linspace(-6.435, 10.4934, 5000)
orbit1 = KeplerianOrbit(period=1.543, t0=-0.123)
orbit2 = KeplerianOrbit(
period=orbit1.period,
t0=orbit1.t0 + 0.5 * orbit1.period,
r_star=ror,
m_star=1.0,
)
y1 = lc1.get_light_curve(orbit=orbit1, r=ror, t=t).eval()
y2 = lc2.get_light_curve(orbit=orbit2, r=1.0, t=t).eval()
y = lc.get_light_curve(orbit=orbit1, r=ror, t=t).eval()
y_expect = (y1 + f * y2) / (1 + f)
assert np.allclose(y_expect, y, atol=5e-6)
def test_mass_units():
P_earth = 365.256
Tper_earth = 2454115.5208333
inclination_earth = np.radians(45.0)
orbit1 = KeplerianOrbit(
period=P_earth,
t_periastron=Tper_earth,
incl=inclination_earth,
m_planet=units.with_unit(1.0, u.M_earth),
)
orbit2 = KeplerianOrbit(
period=P_earth,
t_periastron=Tper_earth,
incl=inclination_earth,
m_planet=1.0,
m_planet_units=u.M_earth,
)
t = np.linspace(Tper_earth, Tper_earth + 1000, 1000)
rv1 = orbit1.get_radial_velocity(t).eval()
rv_diff = np.max(rv1) - np.min(rv1)
assert rv_diff < 1.0, "with_unit"
rv2 = orbit2.get_radial_velocity(t).eval()
rv_diff = np.max(rv2) - np.min(rv2)
assert rv_diff < 1.0, "m_planet_units"
np.testing.assert_allclose(rv2, rv1)
def test_in_transit():
t = np.linspace(-20, 20, 1000)
m_planet = np.array([0.3, 0.5])
m_star = 1.45
orbit = KeplerianOrbit(
m_star=m_star,
r_star=1.5,
t0=np.array([0.5, 17.4]),
period=np.array([10.0, 5.3]),
ecc=np.array([0.1, 0.8]),
omega=np.array([0.5, 1.3]),
m_planet=m_planet,
)
u = np.array([0.2, 0.3, 0.1, 0.5])
r = np.array([0.1, 0.01])
lc = LimbDarkLightCurve(u)
model1 = lc.get_light_curve(r=r, orbit=orbit, t=t)
model2 = lc.get_light_curve(r=r, orbit=orbit, t=t, use_in_transit=False)
vals = theano.function([], [model1, model2])()
utt.assert_allclose(*vals)
model1 = lc.get_light_curve(r=r, orbit=orbit, t=t, texp=0.1)
model2 = lc.get_light_curve(r=r,
orbit=orbit,
t=t,
texp=0.1,
use_in_transit=False)
vals = theano.function([], [model1, model2])()
utt.assert_allclose(*vals)
def test_simple_light_curve_compare_kepler():
t = np.linspace(0.0, 1, 1000)
# We use a long period, because at short periods there is a big difference
# between a circular orbit and an object moving on a straight line.
period = 1000
t0 = 0.5
r = 0.01
r_star = 1
b = 1 - r / r_star * 3
star = LimbDarkLightCurve(0.2, 0.3)
orbit_keplerian = KeplerianOrbit(period=period,
t0=t0,
b=b,
r_star=r_star,
m_star=1)
duration = (period / np.pi) * np.arcsin(
((r_star + r)**2 - (b * r_star)**2)**0.5 / orbit_keplerian.a).eval()
lc_keplerian = star.get_light_curve(orbit=orbit_keplerian, r=r, t=t)
orbit_simple1 = SimpleTransitOrbit(
period=period,
t0=t0,
b=b,
duration=duration,
r_star=r_star,
ror=r / r_star,
)
lc_simple1 = star.get_light_curve(orbit=orbit_simple1, r=r, t=t)
# Should look similar to Keplerian orbit
assert np.allclose(lc_keplerian.eval(), lc_simple1.eval(), rtol=0.001)
def test_contact_bug():
orbit = KeplerianOrbit(period=3.456, ecc=0.6, omega=-1.5)
t = np.linspace(-0.1, 0.1, 1000)
u = [0.3, 0.2]
y1 = (LimbDarkLightCurve(u[0], u[1]).get_light_curve(orbit=orbit,
r=0.1,
t=t,
texp=0.02).eval())
y2 = (LimbDarkLightCurve(u[0], u[1]).get_light_curve(
orbit=orbit, r=0.1, t=t, texp=0.02, use_in_transit=False).eval())
assert np.allclose(y1, y2)
def test_estimate_minimum_mass(seed=9502):
np.random.seed(seed)
t = np.sort(np.random.uniform(0, 10, 500))
period = 2.345
t0 = 0.5
orbit = KeplerianOrbit(period=period, t0=t0, m_planet=0.01, incl=0.8)
y = orbit.get_radial_velocity(t).eval()
m1 = (orbit.m_planet * orbit.sin_incl).eval()
m2 = estimate_minimum_mass(period, t, y).to(u.M_sun).value
m3 = estimate_minimum_mass(period, t, y, t0s=t0).to(u.M_sun).value
assert np.abs((m1 - m2) / m1) < 0.01
assert np.abs((m1 - m3) / m1) < 0.01
def test_small_star():
pytest.importorskip("batman.transitmodel")
from batman.transitmodel import TransitModel, TransitParams
u_star = [0.2, 0.1]
r = 0.04221468
m_star = 0.151
r_star = 0.189
period = 0.4626413
t0 = 0.2
b = 0.5
ecc = 0.1
omega = 0.1
t = np.linspace(0, period, 500)
r_pl = r * r_star
orbit = KeplerianOrbit(
r_star=r_star,
m_star=m_star,
period=period,
t0=t0,
b=b,
ecc=ecc,
omega=omega,
)
a = orbit.a.eval()
incl = orbit.incl.eval()
lc = LimbDarkLightCurve(u_star[0], u_star[1])
model1 = lc.get_light_curve(r=r_pl, orbit=orbit, t=t)
model2 = lc.get_light_curve(r=r_pl, orbit=orbit, t=t, use_in_transit=False)
vals = theano.function([], [model1, model2])()
assert np.allclose(*vals)
params = TransitParams()
params.t0 = t0
params.per = period
params.rp = r
params.a = a / r_star
params.inc = np.degrees(incl)
params.ecc = ecc
params.w = np.degrees(omega)
params.u = u_star
params.limb_dark = "quadratic"
model = TransitModel(params, t)
flux = model.light_curve(params)
assert np.allclose(vals[0][:, 0], flux - 1)
def test_variable_texp():
t = np.linspace(-20, 20, 1000)
m_planet = np.array([0.3, 0.5])
m_star = 1.45
orbit = KeplerianOrbit(
m_star=m_star,
r_star=1.5,
t0=np.array([0.5, 17.4]),
period=np.array([10.0, 5.3]),
ecc=np.array([0.1, 0.8]),
omega=np.array([0.5, 1.3]),
m_planet=m_planet,
)
u = np.array([0.2, 0.3])
r = np.array([0.1, 0.01])
texp0 = 0.1
lc = LimbDarkLightCurve(u[0], u[1])
model1 = lc.get_light_curve(r=r,
orbit=orbit,
t=t,
texp=texp0,
use_in_transit=False)
model2 = lc.get_light_curve(
r=r,
orbit=orbit,
t=t,
use_in_transit=False,
texp=texp0 + np.zeros_like(t),
)
vals = theano.function([], [model1, model2])()
assert np.allclose(*vals)
model1 = lc.get_light_curve(r=r, orbit=orbit, t=t, texp=texp0)
model2 = lc.get_light_curve(
r=r,
orbit=orbit,
t=t,
texp=texp0 + np.zeros_like(t),
use_in_transit=False,
)
vals = theano.function([], [model1, model2])()
assert np.allclose(*vals)
def rv_injection_worker(task):
logK, logP, t0, sini, t_observed, gammadot_limit = task
ecc = 0
if use_exoplanet:
# slow, and bringing a machine-gun to a knife-fight
orbit = KeplerianOrbit(period=np.exp(logP),
b=0,
t0=t0,
r_star=RSTAR,
m_star=MSTAR)
rv = orbit.get_radial_velocity(t_observed,
K=np.exp(logK),
output_units=u.m / u.s)
_rv = rv.eval() * sini
else:
if ecc != 0:
raise NotImplementedError
# analytic solution for circular orbits (from radvel.kepler)
per = np.exp(logP)
tp = t0
om = 0
k = np.exp(logK)
m = 2 * np.pi * (((t_observed - tp) / per) - np.floor(
(t_observed - tp) / per))
_rv = k * sini * np.cos(m + om)
coef = polyfit(t_observed, _rv, 1)
slope = coef[0]
isdetectable = np.abs(slope) > gammadot_limit.to(u.m / u.s / u.day).value
return slope, isdetectable