def test_hyperbolic_orbits_1(self):
o = Orbit(
i = 0.14170287439640022,
Ω = 3.978394514307273,
ω = 0.22281479333802098,
e = 1.077961355413604,
a = -8856935.204227254,
M0 = -6.003136275330101,
t0 = 34056451.522458464,
body = CelestialBody(
name = 'kerbin',
equatorial_radius = 600000.0,
gravitational_parameter = 3531600035840.0,
rotational_speed = 0.0002908894093707204,
),
)
t = o.epoch
tpe = o.time_to_periapsis_at_epoch
npoints = 10
tmin = t + tpe - 30
tmax = t + tpe + 30
tt = np.linspace(tmin,tmax,npoints)
lat = o.latitude_at_time(tt) / deg
lon = o.longitude_at_time(tt) / deg
r = o.radius_at_time(tt)
def setup_orbit():
b = CelestialBody(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.periapsis = 6600*km
o.speed_at_periapsis = 1.2 * b.escape_speed(6600*km)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.eccentricity = 1
o.periapsis = 7000*km
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.position_at_epoch = (-5368*km, -1784*km, 3691*km)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.position_at_epoch = -6045*km, -3490*km, 2500*km
o.velocity_at_epoch = -3.457*km, 6.618*km, 2.533*km
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.position_at_epoch = (8182.4*km, -6865.9*km, 0)
o.velocity_at_epoch = (0.47572*km, 8.8116*km, 0)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.position_at_epoch = (7000*km, 9000*km, 0)
o.velocity_at_epoch = (-5*km, 7*km, 0)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.position_at_epoch = (7000*km,-12124*km,0)
o.velocity_at_epoch = (2.6679*km,4.6210*km,0)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.position_at_epoch = (1600*km, 5310*km, 3800*km)
o.velocity_at_epoch = (-7.350*km, 0.4600*km, 2.470*km)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.e = 0.3
o.h = 60000*km**2
o.θ0 = 120*deg
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.radius_at_epoch = 14600*km
o.speed_at_epoch = 8.6*km
o.flight_path_angle_at_epoch = 50*deg
return o
def setup_orbit():
b = CelestialBody(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.radius_at_epoch = 7200*km
o.radial_speed_at_epoch = 1*km
o.semi_major_axis = 10000*km
o.i = 0
o.Ω = 0
o.ω = 0
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b,
pe_alt = 500*km,
ap_alt = 5000*km)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
rotational_speed = 72.9217e-6,
)
o = Orbit(body=b)
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
z1 = 1545*km
θ1 = 126*deg
z2 = 852*km
θ2 = 58*deg
return Orbit.from_altitude_at_true_anomaly(z1,θ1,z2,θ2,b)
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
oe = Bunch(
body = b,
periapsis_altitude = 400*km,
apoapsis_altitude = 4000*km,
)
return Orbit(**oe)
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
return Orbit(body=b,
orbit_type = OrbitType.parabolic,
vpe = 10*km,
θ0 = 0,
t0 = 0,
i = 0,
Ω = 0,
ω = 0)
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
return Orbit(body=b,
vpe = 15*km,
pe_alt = 300*km,
θ0 = 0,
t0 = 0,
i = 0,
Ω = 0,
ω = 0)
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b,
epoch = 0,
h = 80000*km**2,
e = 1.4,
i = 30*deg,
Ω = 40*deg,
ω = 60*deg,
θ0 = 30*deg)
return o
def setup_orbit():
return Orbit(
i = 0.14,
Ω = 3.9,
ω = 0.2,
e = 0.1,
a = 8850000,
M0 = 5,
t0 = 34000000,
body = CelestialBody(
name = 'kerbin',
equatorial_radius = 600000.0,
gravitational_parameter = 3531600035840.0,
rotational_speed = 0.0002908894093707204,
),
)
def test_pe_speed(self):
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
ee = np.linspace(0,2,50)
apo = []
vpe = []
for e in ee:
o = Orbit(body=b,pe=7000*km,e=e)
apo.append(o.apoapsis_altitude)
vpe.append(o.speed_at_periapsis)
apo = np.array(apo)/(km*km)
vpe = np.array(vpe)/km
'''
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3,
)
o = Orbit(body=b)
o.pe = 9600*km
o.ap = 21000*km
o.epoch = 0
o.θ0 = 0
return o
def setup_orbit():
b = Bunch(
equatorial_radius = 6378*km,
gravitational_parameter = 398600*km**3)
o = Orbit(body=b)
o.epoch = 0
o.true_anomaly_at_epoch = 30*deg
o.radius_at_epoch = 10000*km
o.speed_at_epoch = 10*km
return o
def test_hyperbolic_orbits_2(self):
# same orbit pulled from KSP at different times
# lots of jitter, so tolerance for radius at time
# is quite large (1%)
o1 = Orbit(
i = 0.14149227768205455,
Ω = 3.977254620789031,
ω = 0.22395653996553322,
e = 1.0779572208620696,
a = -8855744.039847286,
M0 = -6.0078569863130475,
t0 = 34056398.642449796,
body = CelestialBody(
name = 'Kerbin',
equatorial_radius = 600000.0,
gravitational_parameter = 3531600035840.0,
rotational_speed = 0.0002908894093707204,
),
)
o2 = Orbit(
i = 0.14311811324451928,
Ω = 3.9859850089566558,
ω = 0.21660875587091438,
e = 1.07736727693924,
a = -8880527.593801336,
M0 = -0.012499818155590287,
t0 = 34140525.998688884,
body = CelestialBody(
name = 'Kerbin',
equatorial_radius = 600000.0,
gravitational_parameter = 3531600035840.0,
rotational_speed = 0.0002908894093707204,
),
)
tpe1 = o1.time_to_periapsis_at_epoch
tpe2 = o2.time_to_periapsis_at_epoch
self.isclose(o1.epoch+tpe1, o2.epoch+tpe2)
χexpect1 = np.sqrt(-o1.a) \
* (o1.eccentric_anomaly_at_time(o1.epoch+tpe1) \
- o1.eccentric_anomaly_at_epoch)
χexpect2 = np.sqrt(-o2.a) \
* (o2.eccentric_anomaly_at_time(o2.epoch+tpe2) \
- o2.eccentric_anomaly_at_epoch)
tt = np.linspace(o1.epoch,o1.epoch+1*6*60*60,50)
χχexpect = np.sqrt(-o1.a) \
* (o1.eccentric_anomaly_at_time(tt) \
- o1.eccentric_anomaly_at_epoch)
χχ = o1.universal_anomaly_at_time(tt)
t0 = o1.epoch
r0 = o1.radius_at_epoch
vr0 = o1.radial_speed_at_epoch
a = o1.semi_major_axis
x0 = o1.position_at_epoch/km
v0 = o1.velocity_at_epoch
#print('t0',t0)
#print('r0',r0)
#print('vr0',vr0)
#print('a',a)
#print('x0',x0)
#print('v0',v0)
#from matplotlib import pyplot
#pyplot.plot(tt,χχexpect, color='blue')
#pyplot.plot(tt[[0,-1]],χχexpect[[0,-1]], color='lightblue')
#pyplot.plot(tt,χχ, color='red')
#pyplot.plot(tt[[0,-1]],χχ[[0,-1]], color='pink')
#pyplot.show()
#print('θpe1',o1.true_anomaly_at_time(o1.epoch+tpe1))
#print('θpe2',o2.true_anomaly_at_time(o2.epoch+tpe2))
#print('rpeθ1',o1.radius_at_true_anomaly(
#o1.true_anomaly_at_time(o1.epoch+tpe1)))
#print('rpeθ2',o2.radius_at_true_anomaly(
#o2.true_anomaly_at_time(o2.epoch+tpe2)))
f1,g1,df1,dg1 = o1.lagrange_coefficients_at_time(o1.epoch+tpe1)
f2,g2,df2,dg2 = o2.lagrange_coefficients_at_time(o2.epoch+tpe2)
x1 = o1.position_at_lagrange_coefficients(f1,g1)
x2 = o2.position_at_lagrange_coefficients(f2,g2)
#print('rpe1(χexp)',np.sqrt(sum(x1**2)))
#print('rpe2(χexp)',np.sqrt(sum(x2**2)))
self.isclose(o2.periapsis, o2.radius_at_time(o2.epoch+tpe2))
self.isclose(o1.periapsis, o1.radius_at_time(o1.epoch+tpe1))
self.isclose(o1.periapsis, o2.periapsis,rtol=1e-2)
self.isclose(o1.radius_at_time(o1.epoch+tpe1),
o2.radius_at_time(o2.epoch+tpe2),
rtol=0.01)
