Low Thrust Trajectories Using the Two Variable Asymptotic Expansion Method

Citation

Stavro, William C. (1969) Low Thrust Trajectories Using the Two Variable Asymptotic Expansion Method. Engineer's thesis, California Institute of Technology. doi:10.7907/2DZ1-3033. https://resolver.caltech.edu/CaltechETD:etd-03312009-143046

Abstract

An approximate analytic solution is derived in this thesis for the variables which describe a heliocentric low-thrust trajectory. The two-variable asymptotic expansion procedure is used. It is assumed that the thrust acceleration varies as the inverse of the distance to the central body raised to an arbitrary power α. Thus the value of α = 1.4 will represent a solar-electric propulsion system, and the value of α = 0 will represent a nuclear-electric system. It is also assumed that the mass of the spacecraft remains constant and that the direction of the thrust vector is arbitrary but remains constant. The results are compared to numerical integrations and to other integrating low-thrust programs.

Thesis Files