The number of impulses in the coplanar problem of energyoptimized flight between close Keplerian orbits
Abstract
The objective of the study is to determine the maximum number of impulses for the energyoptimized transfer between closely adjacent elliptic Keplerian orbits. It is shown that for an arbitrary eccentricity of the adjacent orbits, only singleimpulse transfers are optimum with respect to energy. An analysis is also made of the coplanar problem of a minimumenergy impulse maneuver for avoiding the intersection of close elliptic Keplerian orbits. It is shown that only singleimpulse maneuvers are optimum for an orbit eccentricity of less than 0.7748, while optimum twoimpulse maneuvers exist for larger eccentricities.
 Publication:

Leningradskii Universitet Vestnik Matematika Mekhanika Astronomiia
 Pub Date:
 October 1985
 Bibcode:
 1985VeLen.......67A
 Keywords:

 Kepler Laws;
 Spacecraft Maneuvers;
 Trajectory Optimization;
 Transfer Orbits;
 Eccentric Orbits;
 Fuel Consumption;
 Orbital Maneuvers;
 Astrodynamics