A method of controlling orbits of geostationary satellites with minimum fuel consumption
Abstract
The orbital angular velocity of a stationary satellite is considered to express the perturbation on an orbit of the satellite, and to draw the conclusion that the minimum variation in direction of this velocity agrees with the minimum fuel consumption to maintain a stationary satellite within allocated bounds. The directional variation of the orbital angular velocity is kept minimum by maintaining the ascending node of the orbit in about the direction of the vernal equinox. The direction of the ascending node with minimum fuel consumption to maintain the orbit is given over 18.6 year nodal period of the moon, over which period the inclination variation of the orbit and the angular speed proportional to the necessary amount of fuel to maintain the orbit are also given. The method in this paper is applicable to geostationary communication satellites, UHF broadcasting satellites, solar power satellites etc.
 Publication:

Radio Research Laboratory, Journal
 Pub Date:
 November 1978
 Bibcode:
 1978RaRLJ..25..247T
 Keywords:

 Fuel Consumption;
 Geosynchronous Orbits;
 Satellite Orbits;
 Satellite Perturbation;
 Synchronous Satellites;
 Angular Velocity;
 Orbit Perturbation;
 Orbital Elements;
 Orbital Mechanics;
 Spin Stabilization;
 Three Axis Stabilization;
 Trajectory Optimization;
 Astrodynamics