JPL Technical Report Server

Optimal Low Thrust Trajectories Using Differential Inclusion Concepts

Show simple item record Williams, S. en_US Coverstone-Carroll, V. en_US 2004-10-04T22:46:37Z 2004-10-04T22:46:37Z 1994-02-14 en_US
dc.identifier.citation Cocoa Beach, Florida, USA en_US
dc.identifier.clearanceno 94-0236 en_US
dc.description.abstract A direct optimization method based on differential inclusion concepts has been developed and used to compute low thrust trajectories. This new formulation removes explicit control dependence from the problem statement thereby reducing the dimension of the parameter space of the resulting nonlinear programming problem. A simple example of a two-dimensional gravity-free trajectory involving a maximum velocity transfer to a rectilinear path is discussed. Three interplanetary trajectory examples, an Earth-Mars constant specific impulse transfer, and Earth-Jupiter constant specific impulse transfer, and an Earth-Venus-Mars variable specific impulse gravity assist, are also included. An analysis of the technique's performance is provided. en_US
dc.format.extent 402997 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other low thrust trajectories differential inclusion concepts asteroid rendezvous comet rendezvous solar probe outer planet orbiters Mercury orbiters Pluto flyby en_US
dc.title Optimal Low Thrust Trajectories Using Differential Inclusion Concepts en_US

Files in this item

This item appears in the following Collection(s)

Show simple item record



My Account