Example - 65 - Probe-Orbiter Deflection Maneuver
In this example, we illustrate the calculation of the orbiter divert maneuver delta-V after probe release.
[1]:
import numpy as np
from AMAT.maneuver import ProbeOrbiterDeflection
The probe will enter near equator, prograde. The orbiter will target a 4000 km periapsis altitude, near equatorial retrograde orbit. The deflection manuever is performed 60 days before probe entry, at a distance of 4225 times the radius of Neptune.
[2]:
deflection = ProbeOrbiterDeflection(arrivalPlanet="NEPTUNE",
v_inf_vec_icrf_kms=np.array([17.78952518, 8.62038536, 3.15801163]),
rp_probe=(24622+400)*1e3, psi_probe=3*np.pi/2, h_EI_probe=1000e3,
rp_space=(24622+4000)*1e3, psi_space=np.pi/2,
r_dv_rp=4225)
Compute the orbit divert maneuver delta-V
[3]:
print("Divert manuever DV: "+str(deflection.dv_maneuver_vec)+ " m/s")
Divert manuever DV: [-1.15867678e+00 1.55142771e+01 -9.20109868e-04] m/s
[4]:
print("Divert manuever DV magnitude: "+str(round(deflection.dv_maneuver_mag,3))+ " m/s")
Divert manuever DV magnitude: 15.557 m/s
[5]:
print("TOF from probe release to atm. entry interface: "+str(round(deflection.TOF_probe,6))+ " days")
print("TOF from probe release to orbiter periapsis : "+str(round(deflection.TOF_space,6))+ " days")
TOF from probe release to atm. entry interface: 60.070866 days
TOF from probe release to orbiter periapsis : 60.071683 days
Run python example-65-probe-orbiter-deflection-viz.py from your virtual env terminal to generate the figure below showing the geometry of the two approach trajectories.
[6]:
from IPython.display import Image
Image(filename="../plots/example-65-probe-orbiter-deflection.png", width=800)
[6]:
