def test_body_from_parameters_raises_valueerror_if_k_units_not_correct():
wrong_k = 4902.8 * u.kg
_name = _symbol = ""
_R = 0
with pytest.raises(u.UnitsError) as excinfo:
Body.from_parameters(None, wrong_k, _name, _symbol, _R)
assert (
"UnitsError: Argument 'k' to function 'from_parameters' must be in units convertible to 'km3 / s2'."
in excinfo.exconly())
def test_body_printing_has_name_and_symbol():
name = "2 Pallas"
symbol = u"\u26b4"
k = 1.41e10 * u.m**3 / u.s**2
pallas2 = Body(None, k, name, symbol)
assert name in str(pallas2)
assert symbol in str(pallas2)
def test_body_from_parameters_returns_body_object():
k = 1.26712763e17 * u.m**3 / u.s**2
R = 71492000 * u.m
_name = _symbol = "jupiter"
jupiter = Body.from_parameters(Sun, k, _name, _symbol, Jupiter.R)
assert jupiter.k == k
assert jupiter.R == R
def test_orbit_from_custom_body_raises_error_when_asked_frame():
attractor = Body(Sun, 1 * u.km**3 / u.s**2, "_DummyPlanet")
r = [1e09, -4e09, -1e09] * u.km
v = [5e00, -1e01, -4e00] * u.km / u.s
ss = Orbit.from_vectors(attractor, r, v)
with pytest.raises(NotImplementedError) as excinfo:
ss.frame
assert ("Frames for orbits around custom bodies are not yet supported"
in excinfo.exconly())
def test_from_relative():
TRAPPIST1 = Body.from_relative(
reference=Sun,
parent=None,
k=0.08, # Relative to the Sun
name="TRAPPIST",
symbol=None,
R=0.114,
) # Relative to the Sun
# Check values properly calculated
VALUECHECK = Body.from_relative(
reference=Earth,
parent=TRAPPIST1,
k=1,
name="VALUECHECK",
symbol=None,
R=1,
)
assert Earth.k == VALUECHECK.k
assert Earth.R == VALUECHECK.R
def test_body_has_k_given_in_constructor():
k = 3.98e5 * u.km**3 / u.s**2
earth = Body(None, k, "")
assert earth.k == k
def test_hill_radius_given_a():
parent = Body(None, 1 * u.km**3 / u.s**2, "Parent")
body = Body(parent, 1 * u.km**3 / u.s**2, "Body")
r_SOI = hill_radius(body, 1 * u.km, 0.25 * u.one)
expected_r_SOI = 520.02096 * u.m
assert_quantity_allclose(r_SOI, expected_r_SOI, rtol=1e-8)
def test_laplace_radius_given_a():
parent = Body(None, 1 * u.km**3 / u.s**2, "Parent")
body = Body(parent, 1 * u.km**3 / u.s**2, "Body")
r_SOI = laplace_radius(body, 1 * u.km)
assert r_SOI == 1 * u.km
import gym
from astropy.time import Time
from gym import spaces
from astropy.coordinates import solar_system_ephemeris
from astropy import units as u
from astropy.constants import g0, G
from poliastro.bodies import Saturn, Body
from poliastro.ephem import Ephem
from poliastro.maneuver import Maneuver
import numpy as np
from poliastro.twobody.orbit import Orbit
from poliastro.util import norm
moon_dict = {
601: {
"body": Body(Saturn, (G * 4e19 * u.kg), "Mimas", R=396 * u.km),
"orbital_radius": 185_537 * u.km,
"soi": None,
"index": [(0, 6), (6, 601)]
},
602: {
"body": Body(Saturn, (G * 1.1e20 * u.kg), "Enceladus", R=504 * u.km),
"orbital_radius": 237_948 * u.km,
"soi": None,
"index": [(0, 6), (6, 602)]
},
603: {
"body": Body(Saturn, (G * 6.2e20 * u.kg), "Tethys", R=1_062 * u.km),
"orbital_radius": 294_619 * u.km,
"soi": None,
"index": [(0, 6), (6, 603)]
def wrapper(t, u_, k, *args, **kwargs):
r, v = u_[:3], u_[3:]
ss = RVState(Body(None, k * u.km3s2, "_Dummy"), r * u.km, v * u.kms)
return func(t, ss, *args, **kwargs)
def wrapper(t, u_, k, *args, **kwargs):
r, v = u_[:3], u_[3:]
ss = RVState(Body(None, k * u.au3s2, "_Dummy"), r * u.au, v * u.aus,
Planes.EARTH_EQUATOR)
return func(t, ss, *args, **kwargs)
def test_compute_soi_given_a():
parent = Body(None, 1 * u.km ** 3 / u.s ** 2, "Parent")
body = Body(parent, 1 * u.km ** 3 / u.s ** 2, "Body")
r_SOI = compute_soi(body, 1 * u.km)
assert r_SOI == 1 * u.km
