Transfer between arbitrary Keplerian orbits using two impulses of fixed magnitude.
Abstract
The paper presents an algorithm for determining the firing directions for two fixedmagnitude impulses that transfer a spacecraft from a specified initial orbit to a specified final orbit. The first impulse (assuming the existence of a solution) places the spacecraft on a transfer orbit which intersects the final orbit, at which point the second impulse leaves the spacecraft in final orbit. The basic theory and the computer program are described, and numerical results are provided.
 Publication:

Israel Journal of Technology
 Pub Date:
 1977
 Bibcode:
 1977IsJT...15...22G
 Keywords:

 Algorithms;
 Kepler Laws;
 Spacecraft Trajectories;
 Trajectory Control;
 Transfer Orbits;
 Circular Orbits;
 Computer Programs;
 Impulses;
 Iterative Solution;
 Orbit Calculation;
 Trajectory Analysis;
 Astrodynamics