Satellite orbit and visibility plots (pymgp.orbplot)

Plot satellite orbits in Earth Centered Inertial (ECI) and as ground tracks in Earth Centered Earth Fixed (ECEF) reference frame, plot information on visibility from an observer, and look angles, range and range-rate.

High level plot functions

pltposvel(t, xsat, vsat[, satid, crs, ax, ...])	Plot satellite position and velocity.
pltsattrack(t, xsat[, satid, xobj, llhobj, ...])	Plot satellite orbit tracks in ECI (right-ascension and declination).
pltgroundtrack(t, xsate[, satid, xobje, ...])	Plot satellite ground track(s).
pltsatview(t, zen, azi, robj2sat, rrobj2sat)	Plot elevation angle, azimuth angle, range and range rate.
skyplot(t, azi, zen[, cutoff, satnames, ax, ...])	Skyplot (polar plot) with elevation and azimuth of satellite(s).
plt3dorbit(t, xsat[, satid, xobj, llhobj, ...])	3D orbit plot in ECI and ECEF.

Low level plot functions

plot_orbit_3D(ax, xsat[, xobj])

Plot 3d orbits of satellites around the Earth.

Plot support functions

rewrap(t, x[, method, wrapat, verbose])	Rewrap cyclic data for plotting line segments.
rewrap2d(x, y[, method, xwrapat, ywrapat, ...])	Rewrap cyclic x and y data for plotting line segments.
xlabels(t)	Prepare x-axis labels and title string entries.

Other functions

plh2ecef(objcrd[, unit])	Convert ECEF latitude, longitude and height to Cartesian coordinates.
plh2eci(t, objcrd[, unit])	Convert ECEF latitude, longitude and height to ECI position and velocity.
ecef2plh(xobje[, unit])	Convert Cartesian coordinates in ECEF to latitude, longitude and height.
obj2sat(xsat, vsat, xobj, vobj)	Compute zenith angle, azimuth, range and range-rate.
xyz2radec(xyz[, unit])	Compute right ascension (ra) and declination (dec).
xyz2zassp(xsat, xobj)	Compute zenith angle, azimuth and distance.
ra2lon(t, ra[, unit])	Convert right ascension in ECI to longitude in ECEF.

The functions are optimized for Python’s numpy library, it accepts mostly numpy alike ndarrays with the coordinates (usually three) in the last axis.