Effects of small thrust on the motion of an artificial Earth satellite
Abstract
Perturbative effects of small thrust on the motion of an artificial Earth satellite are investigated. The Lagrange planetary equations in Gaussian form are applied to determine the variations of the orbital elements. Also, equations of motion expressed in terms of different components of the thrust acceleration are used. It is assumed that the small thrust acceleration is a function of time and expressible as a linear combination of a polynomial and a composite set of all sines and cosines. By the method of linear perturbations the equations are solved and the perturbative effects on satellite orbital elements are obtained. The terms in variations of orbital elements are of three types. They are purely secular, periodic, and mixed secular types. Considering the gravitational disturbing function of the Earth and the lunisolar disturbing function to deal with the combined effect, the theory is applied to the orbit of the geostationary satellite. Then the variations of orbital elements, the longitude, the latitude, and the height based on the standard Earthellipsoid are calculated. In addition, the method of determining the components of the thrust that maintains the longitude and the latitude of the satellite within a given tolerance band about a prespecified station is discussed.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 1982
 Bibcode:
 1982STIN...8324533T
 Keywords:

 Low Thrust;
 Orbital Mechanics;
 Satellite Orbits;
 Satellite Perturbation;
 Equations Of Motion;
 EulerLagrange Equation;
 Gravitational Effects;
 Perturbation Theory;
 Synchronous Satellites;
 Launch Vehicles and Space Vehicles