Changing orbits

Gravity m3/s2
Body radius m
Atmosphere height m
Sphere of Influence m

Start orbit

Semi-major axis m => period of
Eccentricity
Periapsis m = mASL = m above atmosphere , m/s
Apoapsis m = mASL = m above atmosphere , m/s
Argument of periapsisº
Inclinationº
Longitude of ascending nodeº
Mean anomaly at epochº

Transfer

Target orbit

Semi-major axis m => period of
Eccentricity
Periapsis m = mASL = m above atmosphere , m/s
Apoapsis m = mASL = m above atmosphere , m/s
Argument of periapsisº
Inclinationº
Longitude of ascending nodeº
Mean anomaly at epochº