def test_compare_constant_theta_thrust_to_rv(self):
X0_meeMl0 = meeMl0_0
X0_rv = rv_0
u = np.array([[0., 1e-6, 0.]])
kep_dyn_meeMl0 = meeMl0.KeplerianDynamics()
conthrust_meeMl0 = meeMl0.ConstantThrust(u)
sysmeeMl0 = utl.SystemDynamics(kep_dyn_meeMl0, conthrust_meeMl0)
kep_dyn_rv = rv.KeplerianDynamics()
conthrust_rv = rv.ConstantThrust(u)
sysrv = utl.SystemDynamics(kep_dyn_rv, conthrust_rv)
segments = orbits * segs_per_orbit
domains = [k * period / segs_per_orbit for k in range(segments + 1)]
seg_number = len(domains) - 1
N = (order_mcpi, ) * seg_number
mcpi_meeMl0 = mcpyi.MCPI(sysmeeMl0, domains, N, 'warm', X0_meeMl0, tol)
mcpi_rv = mcpyi.MCPI(sysrv, domains, N, 'warm', X0_rv, tol)
X_meeMl0 = mcpi_meeMl0.solve_serial()(T)
X_rv = mcpi_rv.solve_serial()(T)
np.testing.assert_allclose(X_rv,
convert.rv_mee(
convert.mee_meeMl0(T, X_meeMl0)),
rtol=0,
atol=tol * 10)
def test_compare_zonal_to_rv(self):
X0_meeMl0 = meeMl0_0
X0_rv = rv_0
order_H = 6
kep_dyn_meeMl0 = meeMl0.KeplerianDynamics()
zon_grav_meeMl0 = meeMl0.ZonalGravity(order=order_H)
sysmeeMl0 = utl.SystemDynamics(kep_dyn_meeMl0, zon_grav_meeMl0)
kep_dyn_rv = rv.KeplerianDynamics()
zon_grav_rv = rv.ZonalGravity(order=order_H)
sysrv = utl.SystemDynamics(kep_dyn_rv, zon_grav_rv)
segs_per_orbit = 6
segments = orbits * segs_per_orbit
domains = [k * period / segs_per_orbit for k in range(segments + 1)]
seg_number = len(domains) - 1
N = (order_mcpi, ) * seg_number
mcpi_meeMl0 = mcpyi.MCPI(sysmeeMl0, domains, N, 'warm', X0_meeMl0, tol)
mcpi_rv = mcpyi.MCPI(sysrv, domains, N, 'warm', X0_rv, tol)
X_meeMl0 = mcpi_meeMl0.solve_serial()(T)
X_rv = mcpi_rv.solve_serial()(T)
np.testing.assert_allclose(X_rv,
convert.rv_mee(
convert.mee_meeMl0(T, X_meeMl0)),
rtol=0,
atol=tol * 10)
def __call__(self, T, X):
"""Calculate zonal gravity perturations for MEEs with Ml0.
Args:
T: ndarray
(m, 1) array of times.
X: ndarray
(m, 6) array of modified equinoctial elements ordered as
(p, f, g, h, k, Ml0), where
p = semi-latus rectum
f = 1-component of eccentricity vector in perifocal frame
g = 2-component of eccentricity vector in perifocal frame
h = 1-component of the ascending node vector in equ. frame
k = 2-component of the ascending node vector in equ. frame
Ml0 = mean longitude at epoch
Returns:
Xdot: ndarray
(m, 6) array of state derivatives.
"""
super().lvlh_acceleration(T, convert.rv_mee(convert.mee_meeMl0(T, X)))
G = GVE()(T, X)
m = T.shape[0]
return (G @ self.a_lvlh.reshape((m, 3, 1))).reshape((m, 6))
def test_mee_meeMl0_mee(self):
T = np.linspace(0, 10, num=m)
mee = convert.mod_angles(convert.mee_coe(coe_sltn))
meeMl0 = convert.meeMl0_mee(T, mee)
mee2 = convert.mod_angles(convert.mee_meeMl0(T, meeMl0))
diff = convert.mod_angles(np.abs(mee - mee2), angle_indices=[5])
indices_2pi = np.where(2 * np.pi - tol < diff)
diff[indices_2pi] -= 2 * np.pi
np.testing.assert_allclose(diff, 0., rtol=0, atol=tol)
def test_compare_keplerian_to_rv(self):
X0_meeMl0 = meeMl0_0
X0_rv = rv_0
X_meeMl0 = meeMl0.KeplerianSolution(X0_meeMl0)(T)
X_rv = rv.KeplerianSolution(X0_rv)(T)
np.testing.assert_allclose(convert.rv_mee(
convert.mee_meeMl0(T, X_meeMl0)),
X_rv,
rtol=0,
atol=tol * 10)
def test_compare_dynamics_to_rv(self):
X0_meeMl0 = meeMl0_0
X0_rv = rv_0
meeMl0_dyn = meeMl0.KeplerianDynamics()
rv_dyn = rv.KeplerianDynamics()
segments = orbits * segs_per_orbit
domains = [k * period / segs_per_orbit for k in range(segments + 1)]
seg_number = len(domains) - 1
N = (order_mcpi, ) * seg_number
mcpi_meeMl0 = mcpyi.MCPI(meeMl0_dyn, domains, N, 'warm', X0_meeMl0,
tol)
mcpi_rv = mcpyi.MCPI(rv_dyn, domains, N, 'warm', X0_rv, tol)
X_meeMl0 = mcpi_meeMl0.solve_serial()(T)
X_rv = mcpi_rv.solve_serial()(T)
np.testing.assert_allclose(X_rv,
convert.rv_mee(
convert.mee_meeMl0(T, X_meeMl0)),
rtol=0,
atol=tol * 10)
def __call__(self, T, X):
"""Calculate Hamiltonian.
Args:
T: ndarray
(m, 1) array of times.
X: ndarray
(m, 6) array of modified equinoctial elements ordered as
(p, f, g, h, k, Ml0), where
p = semi-latus rectum
f = 1-component of eccentricity vector in perifocal frame
g = 2-component of eccentricity vector in perifocal frame
h = 1-component of the ascending node vector in equ. frame
k = 2-component of the ascending node vector in equ. frame
Ml0 = mean longitude at epoch
Returns:
H_rel: ndarray
(m, 1) array of Hamiltonian over time.
"""
Hamiltonian = rvHam(mu=self.mu, order=self.order, r_earth=self.r_earth)
return Hamiltonian(
T, convert.rv_mee(convert.mee_meeMl0(T, X, mu=self.mu)))