Stavro, William C. (1969) Low thrust trajectories using the two variable asymptotic expansion method. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-03312009-143046
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.
|Item Type:||Thesis (Engineer's thesis)|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||20 May 1969|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||31 Mar 2009|
|Last Modified:||26 Dec 2012 02:36|
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