Optimization of low thrust trajectories for collinear Lagrange point mission
Abstract
Two kinds of optimization problems on low thrust transfer trajectories are discussed. One is a transfer from Earth parking orbit to SunEarth interior libration point I (sub 1). So called Jminimum trajectories are obtained for this case. It is shown that, in spite of some injection error, spacecraft can reach L (sub 1) by optimizing low thrust programs. The other problem pertains to a transfer between collinear Lagrange points, L (sub 1) and L (sub 2) of SunEarth system. In this case, two types of low thrust, that is, power constant and thrust constant trajectories are studied. In the former case, Jminimum trajectories are obtained, and, in the latter, fuel optimum trajectories with a single coasting arc were sought including optimal steering programs as a function of total mission time. Computational results show that spacecraft can travel between two points within a mission time that stands comparison with high thrust impulsive transfer.
 Publication:

Symposium on Mechanics for Space Flight
 Pub Date:
 March 1983
 Bibcode:
 1983msf..symp...87M
 Keywords:

 Flight Mechanics;
 Lagrangian Equilibrium Points;
 Spacecraft Trajectories;
 Trajectory Optimization;
 Boundary Value Problems;
 NewtonRaphson Method;
 Three Body Problem;
 Transfer Orbits;
 Velocity Distribution;
 Astrodynamics