Six elements define the earth orbiting artificial satellites.
a
|
Semi
major axis
|
Determine
shape of ellipse
|
e
|
Eccentricity
|
Determine
shape of ellipse
|
Mo
|
Mean
anomaly
|
Gives
the position of the satellite in its orbit at a reference time known as the
epoch
|
ω
|
Argument
of perigee
|
Gives
the rotation of the orbit’s perigee point relative to the orbit’s line of
nodes in the earth’s equatorial plane
|
i
|
Inclination
|
Relate
the orbital plane’s position to the earth
|
Ω
|
Right ascension of the ascending node
|
Relate
the orbital plane’s position to the earth
|
Line of apsides:- The
line joining the perigee (point of closest approach to earth) and apogee (point farthest from earth) through
the center of the earth.
Ascending node:- is
the point where the orbit crosses the
equatorial plane going from south to north whereas Descending
node:- is the point where the orbit crosses the equatorial plane going
from north to south
Line
of nodes:- The line joining the
ascending and descending nodes through the center of the earth.
