Friday, February 12, 2021

Orbital Elements

 Orbital Elements:

  • Earth-orbiting artificial satellites are defined by six orbital elements referred to as the keplerian element set.  
  • Two of these, the semimajor axis a and the eccentricity e, give the shape of the ellipse.  
  • A third, the mean anomaly M0, gives the position of the satellite in its orbit at a reference time known as the epoch.
  •  A fourth, the 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.  
  • The remaining two elements, the inclination i and the right ascension of the ascending node, relate the orbital plane’s position to the earth
Apogee and Perigee Heights:
  • The length of the radius vectors at apogee and perigee can be obtained from the geometry of the ellipse: 

  • In order to find the apogee and perigee heights, the radius of the earth must be subtracted from the radii lengths, as shown in the following example.


If you have any doubts,please let me know