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Acquisition and control of a precision formation flying mission

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dc.contributor.advisor David W. Miller and Alvar Saenz-Otero. en_US
dc.contributor.author Field, John M., S.M. Massachusetts Institute of Technology en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.date.accessioned 2010-10-29T13:50:34Z
dc.date.available 2010-10-29T13:50:34Z
dc.date.copyright 2010 en_US
dc.date.issued 2010 en_US
dc.identifier.uri http://hdl.handle.net/1721.1/59558
dc.description Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010. en_US
dc.description This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections. en_US
dc.description Cataloged from student submitted PDF version of thesis. en_US
dc.description Includes bibliographical references (p. 103-105). en_US
dc.description.abstract Using 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.statementofresponsibility by John M. Field. en_US
dc.format.extent 105 p. en_US
dc.language.iso eng en_US
dc.publisher Massachusetts Institute of Technology en_US
dc.rights M.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.uri http://dspace.mit.edu/handle/1721.1/7582 en_US
dc.subject Aeronautics and Astronautics. en_US
dc.title Acquisition and control of a precision formation flying mission en_US
dc.type Thesis en_US
dc.description.degree S.M. en_US
dc.contributor.department Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.identifier.oclc 668214381 en_US


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