Orbital Elements
Convert an inertial Cartesian state vector into classical orbital elements. The default case is a standard textbook Earth-orbit example.
Position vector r (km)
Velocity vector v (km/s)
Classical elements
Orbit type
Elliptic
Retrograde plane
Semi-major axis
8788.1 km
e = 0.17121
Orientation
i 153.25 deg
RAAN 255.28 deg, omega 20.07 deg
Spacecraft location
nu 28.45 deg
r = 7414.3 km, v = 7.884 km/s
Periapsis radius
7283.5 km
Apoapsis radius
10292.7 km
Period
8198.9 s
3D orbital geometry
Inclination, RAAN, periapsis direction, and current radius are easiest to read in space.
Blue path
elliptic osculating conic
Purple line
RAAN 255.28 deg
Yellow radius
nu 28.45 deg
Plane tilt
i 153.25 deg
Open Source and Easy to Use Elsewhere
This tool is open source and the underlying logic is fully transparent. You can inspect the code, understand the calculations, and contribute improvements. If you want to use the tool in your own website, course page, or learning platform, you can also embed it directly and start from a ready-made iframe setup for this exact tool.
Open source: review the implementation and see how the results are produced.
Embeddable: preview this tool, copy the iframe, and use it in your own site or LMS.