This paper describes the controlled alteration of a spacecraft's orbital elements using low-thrust propulsion. It starts with a general consideration of the problem based upon Lagrange's equations and then examines its reduction to address the quasi-circular orbits appropriate to satellite emplacement. Following this, the paper describes the optimization of low-thrust manoeuvers and extends this to show that constant thrust angle techniques may be used to obtain near-optimum wedge angle and radius alterations. The alteration of ascending node is then addressed, in particular showing how the node may be altered by combined changes to inclination and altitude. This is illustrated by considering an optimum transfer between polar orbits.
Ascending node alteration of polar orbiting spacecraft using low-thrust propulsion
2000-05-01
9 pages
Article (Journal)
Electronic Resource
English
Ascending node alteration of polar orbiting spacecraft using low-thrust propulsion
Online Contents | 2000
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