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Central body the satellite is orbiting.
Mass of the celestial body the satellite is orbiting
Radius of the celestial body.
Closest distance from surface of central body to satellite.
Furthest distance from surface of central body to satellite.
satcatalog: python equatorial_orbit_designer.py radius_perigee = 350.0 km + 6378.1366 km radius_perigee = 6728.1366 km radius_apogee = 400.0 km + 6378.1366 km radius_apogee = 6778.1366 km eccentricity = (6778.1366 km - 6728.1366 km) / (6778.1366 km + 6728.1366 km) eccentricity = 0.003702 semi_major_axis = (6728.1366 km + 6778.1366 km) / 2 semi_major_axis = 6753.1366 km velocity_perigee = sqrt(((2 x 398613.89) / 6728.1366) - (398613.89 / 6753.1366)) velocity_perigee = 7.71 km/s velocity_apogee = sqrt(((2 x 398613.89) / 6778.1366) - (398613.89 / 6753.1366)) velocity_apogee = 7.71 km/s orbital_period = 2 x 3.1416 x sqrt((6753.1366^3) / 398613.89) orbital_period = 92.05 s eclipse_fraction = (3.1416-2 x arccos(6378.1366 / ((6728.1366 + 6778.1366) / 2))) / (2 x 3.1416) eclipse_fraction = 0.3934 eclipse_duration = 0.3934 x 5522.83 sec eclipse_duration 2172.82 sec
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