Orbital elements offer an excellent means of keeping track of earth orbiting satellites. However, in order to find the satellite in the sky ant any given time, these elements need to be transformed into a Cartesian coordinate system. his transformation is relatively simple once we can understand the motion of the satellite geometrically. To start with the satellite moves in a plane which goes through the center of the earth. The direction of this plane is determined by three angles, the argument of thw perigee ,
the right ascension of the node
, and the angle of inclination
.We start with a Cartesian coordinate system with coordinates
in which the
-coordinate is along the semi-major axis of the ellipse pointing toward the perigee, the
-coordinate is perpendicular to the
axis in the plane of motion, and the
- coordinate is normal to this plane. The origin is fixed at the center of the earth. Using Kepler's equation we get the eccentric anomaly
from the mean anomaly
, and can give the Cartesian coordinates of the satellite in the coordinate system
:
We can make this more efficient by describing it via the rotation matrix
To continue our coordinate transformation we need to rotate the system about the
-axis (which is also the line of nodes) by an angle of
, this will give us the coordinates
in a Cartesian coordinate system in which the
axis is along the axis of the earth and the
axis is along the line of nodes. Following our discussion above this transformation is given by