Title page for ETD etd-02132009-171146
|Type of Document
||Kruep, John M.
||Six degree of freedom optimal trajectories for satellite rendezvous
||Master of Science
|Lutze, Frederick H. Jr.
|Anderson, Mark R.
|Durham, Wayne C.
|Date of Defense
A method is developed for computing the minimum fuel trajectory for a satellite
that moves between two different positions and orientations using a sequence of impulsive
burns. The method makes use of the linear Clohessy-Wiltshire equations to describe
translational motions, Euler's equations of rigid body motion for describing the attitude
motions, and a sequential quadratic programming optimization code. Initial solutions are
found assuming no coupling between the translational and rotational motions and with no
imposed constraint on the time of the rendezvous. Further solutions are then found by
varying the vehicle center of gravity location along one axis, thereby coupling the
rotational motions into two axes of translation thrusters, and by imposing time limits on
the rendezvous. A discussion of the impact that these parameters have on the optimal
solutions for two different models of the satellite thruster systems is then presented.
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