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 Sun-Earth interior libration point I (sub 1). So called J-minimum 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 Sun-Earth system. In this case, two types of low thrust, that is, power constant and thrust constant trajectories are studied. In the former case, J-minimum 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;
- Newton-Raphson Method;
- Three Body Problem;
- Transfer Orbits;
- Velocity Distribution;
- Astrodynamics