Package: orpytal
OrPytalOrPytal is an Python package for orbital mechanics. It began as a pet project to find a way to easily create two-body orbits and states, without needing a particular set of parameters. For example, what if you wanted to know what an orbit would look like with a particular radius of apoapsis and specific energy? How about semilatus rectum and eccentricity? OrPytal makes these problems trivial and syntactically easy.Very incomplete documentation can be foundhereA quick exampleThe following examle shows just how easy it is to create orbits and states using OrPytalimport orpytal as op

orbit = op.Orbit(op.bodies.saturn)
orbit.p = 41000 * op.units.miles
orbit.e = 0.9

# Alternatively op.Orbit(op.bodies.saturn, p=41000*op.units.miles, e=0.9)

example_state = orbit.get_state(t_since_rp=orbit.period/2)

print(example_state)The resulting output is-------------------------------------------------------------------------------------------------------
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                                          Keplarian State Data                                         
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                                            Meta Information                                           
  Orbit Name: .................
  State Name: .................
Central Body: Saturn
        Type: Elliptic
  Equitorial: .................
   Ascending: True
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                                            State Parameters                                           
    Pos. Mag. |r|:  6.5983104000e+05         km |          True Anomaly:  3.1415926536e+00        rad |     
    Vel. Mag. |v|:  2.3976288910e+00       km/s |     Eccentric Anomaly:  3.1415926536e+00        rad |     
Flight Path Angle:  0.0000000000e+00        rad |          Mean Anomaly:  3.1415926536e+00        rad |     
Flight Path Angle:  0.0000000000e+00        rad |       Hyperb. Anomaly: ................. .......... |     
 Time Since Peri.:  1.0439272879e+05          s |      Arg. of Latitude: ................. .......... |     
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                                            Perifocal Frame                                            
         Position: ................. .......... |              Velocity: ................. .......... |     
                e: -6.5983104000e+05         km |                     e: -2.9362485470e-15       km/s |     
                p:  8.0805997111e-11         km |                     p: -2.3976288910e+00       km/s |     
                h:  0.0000000000e+00         km |                     h:  0.0000000000e+00       km/s |     
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                                            Orbit Parameters                                           
     Eccentricity:  9.0000000000e-01         nd |           Inclination: ................. .......... |     
   Semimajor Axis:  3.4727949474e+05         km |        Ascending Node: ................. .......... |     
   Semiminor Axis:  1.5137562227e+05         km |      Arg of Periapsis: ................. .......... |     
   Rad. Periapsis:  3.4727949474e+04         km |         Rad. Apoapsis:  6.5983104000e+05         km |     
 Semilatus Rectum:  6.5983104000e+04         km |      Angular Momentum:  1.5820299647e+06     km^2/s |     
      Mean Motion:  3.0093979629e-05      rad/s |        Orbital Period:  2.0878545758e+05          s |     
  Specific Energy: -5.4611930842e+01   km^2/s^2 |           Flyby Angle: ................. .......... |     
       V Infinity: ................. .......... |           TA Infinity: ................. .......... |     
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