Nonsingular and nonconventional orbit perturbation equations
Abstract
The derivation of equations for fast orbital elements describing a perturbed orbital motion is discussed. The criteria necessary to select an appropriate set of orbital parameters are presented together with the equations necessary for determining the evolution of a satellite's position vector within an inertial reference frame. Nonsingular perturbation equations for nearcircular and nearequatorial orbits are presented; the use of quasiangles and difference elements are described. The derivation of nonconventional perturbation equations for quasislow elements in nearcircular and nearequatorial orbits is obtained and an example revealing the applicability of the theory is provided.
 Publication:

Zeitschrift fur Flugwissenschaften und Weltraumforschung
 Pub Date:
 August 1985
 Bibcode:
 1985ZFlWe...9..217V
 Keywords:

 EulerLagrange Equation;
 Orbit Calculation;
 Orbit Perturbation;
 Orbital Elements;
 Satellite Orbits;
 Circular Orbits;
 Equatorial Orbits;
 Orbital Mechanics;
 Perturbation Theory;
 Singularity (Mathematics);
 Astrodynamics