def test_R_A_A_N():
r""" Test for RAAN Function
"""
n_vector = [.25, .5, .75]
actual_out = RV2COE.R_A_A_N(n_vector)
expected_out = 1.1071487177940904
np.testing.assert_allclose(actual_out, expected_out)
def test_line_of_nodes():
r""" Test for Line of Nodes Function
"""
h_hat = [1, 2, 3]
actual_out = RV2COE.line_of_nodes(h_hat)
expected_out = [-2, 1, 0]
np.testing.assert_allclose(actual_out, expected_out)
def test_unit_vector():
r""" Test for the Unit Vector Function
"""
vector = [1, 1, 1]
actual_out = RV2COE.unit_vector(vector)
expected_out = [1 / np.sqrt(3), 1 / np.sqrt(3), 1 / np.sqrt(3)]
np.testing.assert_allclose(actual_out, expected_out)
def test_inclination():
r""" Test for Inclination Function
"""
h_hat = [.25, .75, .5]
actual_out = RV2COE.inclination(h_hat)
expected_out = 1.0471975511965976
np.testing.assert_allclose(actual_out, expected_out)
def test_semi_latus_rectum():
r""" Test for Semi Latus Rectum Function
"""
mu = 10
h_vector = [-3, 6, -3]
actual_out = RV2COE.semi_latus_rectum(mu, h_vector)
expected_out = 5.4
np.testing.assert_allclose(actual_out, expected_out)
def test_ang_momentum():
r""" Test for Angular Momentum Function
"""
r_vector = [1, 2, 3]
v_vector = [4, 5, 6]
actual_out = RV2COE.ang_momentum(r_vector, v_vector)
expected_out = [-3, 6, -3]
np.testing.assert_allclose(actual_out, expected_out)
def test_Orbit_Period():
r""" Test for Orbital Period Function
"""
mu = 2
a = 2
actual_out = RV2COE.Orbit_Period(mu, a)
expected_out = 12.5663706144
np.testing.assert_allclose(actual_out, expected_out)
def test_rad_apo():
r""" Test for Radius of Apoapsis Function
"""
p = 1
e = .5
actual_out = RV2COE.rad_apo(p, e)
expected_out = 2
np.testing.assert_allclose(actual_out, expected_out)
def test_rad_peri():
r""" Test for Radius of Periapsis Function
"""
p = 1
e = .5
actual_out = RV2COE.rad_peri(p, e)
expected_out = .6666666666666
np.testing.assert_allclose(actual_out, expected_out)
def test_semi_major_axis():
r""" Test for Semi Major Axis Function
"""
p = .75
e = .5
actual_out = RV2COE.semi_major_axis(p, e)
expected_out = 1
np.testing.assert_allclose(actual_out, expected_out)
def test_flight_ang():
r""" Test for Radius of Apoapsis Function
"""
e = .5
theta = 1.2
actual_out = RV2COE.flight_ang(e, theta)
expected_out = 0.37578860669992659
np.testing.assert_allclose(actual_out, expected_out)
def test_spec_mech_energy():
r""" Test for Angular Momentum Function
"""
mu = 10
r_vector = [1, 2, 3]
v_vector = [4, 5, 6]
actual_out = RV2COE.spec_mech_energy(mu, r_vector, v_vector)
expected_out = (77 / 2) - (10 / np.sqrt(14))
np.testing.assert_allclose(actual_out, expected_out)
def test_arg_of_periapsis():
r""" Test for Argument of Periapsis Function
"""
r_vector = [1, 2, 3]
h_vector = [-3, 6, -3]
e_vector = [2, 3, 4]
actual_out = RV2COE.arg_of_periapsis(r_vector, e_vector, h_vector)
expected_out = 0.12186756768575521
np.testing.assert_allclose(actual_out, expected_out)
def test_true_anom():
r""" Test for True Anomaly Function
"""
r_vector = [1, 2, 3]
h_vector = [-3, 6, -3]
e_vector = [2, 3, 4]
actual_out = RV2COE.true_anom(r_vector, h_vector, e_vector)
expected_out = -0.12186756768575521
np.testing.assert_allclose(actual_out, expected_out)
def test_eccentricity():
r""" Test for Eccentricity Function
"""
mu = 10
r_vector = [1, 2, 3]
v_vector = [4, 5, 6]
h_vector = [-3, 6, -3]
actual_out = RV2COE.eccentricity(mu, r_vector, v_vector, h_vector)
expected_out = [(-51 / 10) - (1 / np.sqrt(14)), (-3 / 5) - np.sqrt(2 / 7),
(39 / 10) - (3 / np.sqrt(14))]
np.testing.assert_allclose(actual_out, expected_out)
pv_eci = np.dot(ecef2eci, pv_ecef)
"""Rotate rad_r"""
rad_r_eci = np.dot(ecef2eci, rad_r_ecef)
"""Find R and V"""
w_E = [0, 0, 0.000072921151467]
r_eci_array = pr_eci + rad_r_eci
r_eci = [r_eci_array[0][0], r_eci_array[1][0], r_eci_array[2][0]]
v_eci_array = pv_eci.transpose() + np.cross(w_E, r_eci)
v_eci = np.array(
[v_eci_array[0][0], v_eci_array[0][1], v_eci_array[0][2]])
a, e, e_vector, i, raan, w, theta, p, r_p, r_a, n_vector, period = RV2COE.RV2COE(
r_eci, v_eci, mu)
r"""Print The Results in Full"""
Line_3 = ["Semi Major Axis in Kilometers:\n\t", str(a), "\n"]
Line_4 = ["Eccentricity:\n\t", str(e), "\n"]
Line_5 = ["Eccentricity Vector:\n\t", str(e_vector), "\n"]
Line_6 = ["Inclination in Degrees:\n\t", str(np.rad2deg(i)), "\n"]
Line_7 = ["RAAN in Degrees:\n\t", str(np.rad2deg(raan)), "\n"]
Line_8 = [
"Argument of Periapsis in Degrees:\n\t",
str(np.rad2deg(w)), "\n"
]
Line_9 = [
"True Anomaly in Degrees:\n\t",
str(np.rad2deg(theta)), "\n"
]
Line_10 = ["Semi Latus Rectum in Kilometers:\n\t", str(p), "\n"]
Line_0 = ['Line {}\n\t{}\n'.format(count+1,line)]
r_i = float(line[0])
r_j = float(line[1])
r_k = float(line[2])
v_i = float(line[3])
v_j = float(line[4])
v_k = float(line[5])
r_input = [r_i, r_j, r_k]
v_input = [v_i, v_j, v_k]
Line_1 = ("The mu Constant: \n\t", str(mu), "\n", 'Radius {} (km)\n\t{}\n'.format(count+1,r_input))
Line_2 = ('Velocity {} (km/s)\n\t{}\n'.format(count+1,v_input))
r"""Inner Workings, Pulling outside functions"""
h_input = RV2COE.ang_momentum(r_input, v_input)
e_vector = RV2COE.eccentricity(mu, r_input, v_input, h_input)
n_vector = RV2COE.line_of_nodes(RV2COE.unit_vector(h_input))
p = RV2COE.semi_latus_rectum(mu, h_input)
theta = RV2COE.true_anom(r_input, h_input, e_vector)
i = RV2COE.inclination(RV2COE.unit_vector(h_input))
a = RV2COE.semi_major_axis(p, np.linalg.norm(e_vector))
raan = RV2COE.R_A_A_N(n_vector)
r_k = float(line[2])
v_i = float(line[3])
v_j = float(line[4])
v_k = float(line[5])
change_t = float(line[6]) * 60
r_input = np.array([r_i, r_j, r_k])
v_input = np.array([v_i, v_j, v_k])
Line_1 = ("The mu Constant: \n\t", str(mu), "\n",
'Original Radius {} (km)\n\t{}\n'.format(count + 1, r_input))
Line_2 = ('Original Velocity {} (km/s)\n\t{}\n'.format(
count + 1, v_input))
a_i, e_i, e_vector, i_i, raan_i, w_i, theta_i, p, r_p, r_a, n_vector, period = RV2COE.RV2COE(
r_input, v_input, mu)
a_f, e_f, i_f, raan_f, w_f, theta_f = PROPAGATE.update(
a_i, e_i, i_i, raan_i, w_i, theta_i, change_t, mu)
r_eci, v_eci = PROPAGATE.COE2RV(a_f, e_f, i_f, raan_f, w_f, theta_f,
mu)
r"""Print The Results in Full"""
Line_3 = ["Semi Major Axis in Kilometers:\n\t", str(a_f), "\n"]
Line_4 = ["Eccentricity:\n\t", str(e_f), "\n"]
Line_5 = ["Eccentricity Vector:\n\t", str(e_vector), "\n"]
Line_6 = [
"Initial Inclination in Degrees:\n\t",
str(np.rad2deg(i_i)), "\n"
]
Line_7 = [