Near-optimal real-time spacecraft guidance and control using harmonic potential functions and a modified RRT

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dc.contributor.authorZappulla, Richard II
dc.contributor.authorVirgili-Llop, Josep
dc.contributor.authorRomano, Marcello
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentMechanical and Aerospace Engineering (MAE)
dc.dateFebruary 2017
dc.date.accessioned2017-03-02T00:03:23Z
dc.date.available2017-03-02T00:03:23Z
dc.date.issued2017-02
dc.descriptionTo be published in the proceedings of the 27th AAS/AIAA Spaceflight Mechanics Meeting, San Antonio, TX, Feb. 6-9, 2017en_US
dc.description.abstractA primary requirement for any rendezvous and proximity (RPO) guidance algo- rithm is to ensure mission safety through the generation of collision-free trajec- tories in a fuel-efficient manner. This work presents a real-time hybrid guidance method which fuses the flexibility and robustness of Harmonic Potential Functions with the asymptotically-optimal Rapidly-expanding Random Tree Star method. The proposed method allows to plan trajectories on cluttered environments while producing near-fuel-optimal trajectories. To quantify and validate the performance of this method an experimental campaign is performed utilizing the Naval Post- graduate School POSEIDYN test bed. Lastly, implementation considerations and experimental results are discussed.
dc.identifier.otherAS 17-420
dc.identifier.urihttps://hdl.handle.net/10945/51981
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleNear-optimal real-time spacecraft guidance and control using harmonic potential functions and a modified RRTen_US
dc.typeConference Paper
dspace.entity.typePublication
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