Critical inclinations in satellite theory
Abstract
The main problem of satellite theory is described in polar coordinates by a Hamiltonian function. It is proposed to find a solution of the Hamiltonian function with the following properties: (1) the reference orbit is Keplerian; (2) no restriction is imposed on the eccentricity; in particular, it is exempt of singularities  real or apparent  for small eccentricities; and (3) no restriction is imposed on the inclination; in particular, it is exempt of singularities  real or apparent  for small inclinations; also it is valid even in the neighborhood of inclinations at which the perigee is stationary.
 Publication:

Flight Mechanics/Estimation Theory Symposium
 Pub Date:
 May 1978
 Bibcode:
 1978fmet.symp...28D
 Keywords:

 Orbit Calculation;
 Orbital Mechanics;
 Satellite Orbits;
 Satellite Orientation;
 Hamiltonian Functions;
 Orbital Position Estimation;
 Astrodynamics