2026-09-19T01:23:35Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/973622022-01-13T07:53:53Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
David W. Miller and Alvar Saenz-Otero.
Alvisio, Bruno
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics.
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
2015-06-10T19:13:48Z
2015-06-10T19:13:48Z
2015
2015
http://hdl.handle.net/1721.1/97362
910634554
Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 113-115).
Electromagnetic Formation Flight (EMFF) consists of using electromagnetic forces to position or orient satellites in a relative target location or attitude and achieve a certain target formation on orbit. This thesis introduces the fundamental equations of EMFF and the design of the Resonant Inductive Near-Field Generation System (RINGS). RINGS is a testbed composed of two vehicles that are used to demonstrate EMFF in a 6 DoF environment. In this thesis, a RMS current level controller is modeled and implemented in RINGS to give the system electromagnetic actuation capability. Subsequently, a simulation of RINGS that incorporates an EM dynamics model applicable to two RINGS vehicles operating in close proximity is developed. This model was validated using a set of open-loop maneuvers by comparing it with data obtained from experiments using the RINGS aboard the International Space Station (ISS). Finally, this simulation was used to test linear controllers that incorporate an 'Adaptive Control' approach to achieve system stability for a specific configuration and range of disturbances.
by Bruno Alvisio.
S.M.
127 pages
eng
Massachusetts Institute of Technology
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.
http://dspace.mit.edu/handle/1721.1/7582
Aeronautics and Astronautics.
Development and validation of an Electromagnetic Formation Flight simulation as a platform for control algorithm design
Thesis
application/pdf
Publication
unknown
unknown
<Publication xmlns="https://www.openaire.eu/cerif-profile/1.1/" id="9958814a-3267-427d-ba39-e9b6764259be">
<Type xmlns="https://www.openaire.eu/cerif-profile/vocab/COAR_Publication_Types">http://purl.org/coar/resource_type/c_1843</Type>
<Language>eng</Language>
<Title>Development and validation of an Electromagnetic Formation Flight simulation as a platform for control algorithm design</Title>
<PublishedIn>
<Publication>
</Publication>
</PublishedIn>
<PublicationDate>2015</PublicationDate>
<Authors>
<Author>
<DisplayName>Alvisio, Bruno</DisplayName>
<Affiliation>
<OrgUnit>
</OrgUnit>
</Affiliation>
</Author>
</Authors>
<Editors>
</Editors>
<Publishers>
<Publisher>
<DisplayName>Massachusetts Institute of Technology</DisplayName>
<OrgUnit />
</Publisher>
</Publishers>
<License>http://dspace.mit.edu/handle/1721.1/7582</License>
<Keyword>Aeronautics and Astronautics.</Keyword>
<Abstract>Electromagnetic Formation Flight (EMFF) consists of using electromagnetic forces to position or orient satellites in a relative target location or attitude and achieve a certain target formation on orbit. This thesis introduces the fundamental equations of EMFF and the design of the Resonant Inductive Near-Field Generation System (RINGS). RINGS is a testbed composed of two vehicles that are used to demonstrate EMFF in a 6 DoF environment. In this thesis, a RMS current level controller is modeled and implemented in RINGS to give the system electromagnetic actuation capability. Subsequently, a simulation of RINGS that incorporates an EM dynamics model applicable to two RINGS vehicles operating in close proximity is developed. This model was validated using a set of open-loop maneuvers by comparing it with data obtained from experiments using the RINGS aboard the International Space Station (ISS). Finally, this simulation was used to test linear controllers that incorporate an 'Adaptive Control' approach to achieve system stability for a specific configuration and range of disturbances.</Abstract>
<Access xmlns="http://purl.org/coar/access_right"
>
</Access>
</Publication>