Here you can transform from state vector to Keplerian orbital elements.
Please Enter the state vector (Kms,Kms/sec).
Position vector(x,y,z)in Kms
Velocity vector(x-dot,y-dot,z-dot)in Kms/sec
The Keplerian orbital elements are as follows.
Semi-major axis(Kms):
Eccentricity:
Inclination:
Arg of Perigee:
Right Asc of Asc Node:
Mean Anomaly:
True Anomaly:
Eccentric Anomaly: