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dc.contributor.advisorDavid W. Miller and Alvar Saenz-Otero.en_US
dc.contributor.authorField, John M., S.M. Massachusetts Institute of Technologyen_US
dc.contributor.otherMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.date.accessioned2010-10-29T13:50:34Z
dc.date.available2010-10-29T13:50:34Z
dc.date.copyright2010en_US
dc.date.issued2010en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/59558
dc.descriptionThesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010.en_US
dc.descriptionThis electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.en_US
dc.descriptionCataloged from student submitted PDF version of thesis.en_US
dc.descriptionIncludes bibliographical references (p. 103-105).en_US
dc.description.abstractUsing formation flying spacecraft as space-based interferometers will provide images of unprecedented resolution. Missions such as Stellar Imager plan to use multiple spacecraft in a formation instead of a typical monolithic space telescope, achieving a resolution up to 0.1 milliarcseconds. In order to assemble into a formation, these satellites must first locate each other using limited field-of-view sensors. Once the satellites are in a formation, the path length of the light going to the combiner satellite must be controlled to nanometer levels to produce an image of high quality. One solution to control to such precision is to use staged control methods, utilizing multiple actuators with overlapping strokes and bandwidths. This thesis first provides an algorithm for three satellites to initialize into a formation using relative measurements and limited field-of-view sensors. The satellites perform a search to locate each other, accurately point their transmitters at each other, and move into an equilateral triangle formation. This thesis also provides the framework for developing a staged pointing and phasing testbed using the Synchronized Position Hold Engage Reorient Experimental Satellites (SPHERES) as the coarse stage. The pointing actuation is provided by a fast steering mirror and a linear stage, and the phasing actuation is provided by an optical delay line consisting of a voice coil mirror and a piezo mirror.en_US
dc.description.statementofresponsibilityby John M. Field.en_US
dc.format.extent105 p.en_US
dc.language.isoengen_US
dc.publisherMassachusetts Institute of Technologyen_US
dc.rightsM.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.en_US
dc.rights.urihttp://dspace.mit.edu/handle/1721.1/7582en_US
dc.subjectAeronautics and Astronautics.en_US
dc.titleAcquisition and control of a precision formation flying missionen_US
dc.typeThesisen_US
dc.description.degreeS.M.en_US
dc.contributor.departmentMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.en_US
dc.identifier.oclc668214381en_US


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