Prelaunch Analysis Of High Eccentricity Orbits

This paper discusses some applications of Halphen's method for determining the long range (secular) perturbations for planetary and cometary type orbits. This method of treating secular planetary effects has been suggested by Musen for the determination of the long range perturbations due to the moon for artificial satellite orbits. Two FORTRAN II computer programs incorporating this method are described and representative results are presented. The comparison of results obtained here with those obtained by applying other methods demonstrates the adequacy of this method for minor planets and appropriate artificial satellites. It shows also that considerable saving in computer time can be made in the study of artificial satellite orbits when the short period perturbations are not of interest by using a program based on Halphen's method rather than one based on the use of an unaveraged disturbing function. The program for artificial satellites is given.