API

TwoBody API exploration

Classes:

Group 1:

• OrbitalElements
• |----KeplerElements (e, a, i, Omega, omega, M0) the (eccentricity, semimajor axis, inclination, longitude of ascending node, argument of periapsis, mean anomaly at some reference time)
• |----DelaunayElements (l, omega, Omega, ...)??
• |----TheJokerElements? (e, P, ...)

Instead of specifying M0 and time, specify M or other anomaly's directly?

Group 2:

• KeplerOrbit

API:

elem = KeplerElements(e=0.5, ...)
orb = KeplerOrbit(elem)
orb = KeplerOrbit(e=0.5, i=..., elements='kepler') # default

orb.rv(t=t)
orb.rv(mean_anomaly=M)

orb.astrometric(t=t)

TODO:

A way to get out transformed elements?