The use of low thrust devices with continuous and discontinuous thrust programs is investigated to determine whether or not a discontinuous thrust program will provide a greater payload and structure mass fraction, where the program must impart a specified amount of energy to the satellite in a specified total time, starting from a circular parking orbit. A discontinuous thrust program is developed, based on the elliptic orbit, using a perturbation analysis, and a series solution is obtained which permits investigation of this program up to angles of one radian either side of the perigee of the elliptic orbit. These results are compared with a continuous thrust program which gave a spiral orbit. Under certain conditions, where storage batteries must be carried as part of the payload but are available for use during the thrust program, the discontinuous thrust program is found to provide a greater payload and structure mass fraction. Further investigation at angles greater than one radian either side of perigee appears to be warranted.