Advanced Search
DSpace@MIT

Optimal thruster selection with robust estimation for formation flying applications

Research and Teaching Output of the MIT Community

Show simple item record

dc.contributor.author Yang, Trent, 1979- en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.date.accessioned 2005-09-06T20:43:31Z
dc.date.available 2005-09-06T20:43:31Z
dc.date.copyright 2003 en_US
dc.date.issued 2003 en_US
dc.identifier.uri http://hdl.handle.net/1721.1/26899
dc.description Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2003. en_US
dc.description Includes bibliographical references (p. 145-147). en_US
dc.description.abstract The research goal was to develop a computationally fast mapper that can be easily configured to any spacecraft with various types of actuators. The estimation process must be compatible to the mapper and have a fast yet robust fault detection algorithm. A robust fault detection system must be sensitive to failures without raising any false alarms. The linear program (LP) mapping system presented in this thesis was first introduced by Crawford in 1968 (Ref. 42) and has been since used on a number of vehicle control systems (Ref. 9, Ref. 41). In this paper, several new innovations are developed as extensions to the basic LP. First, a solution scheme is presented to handle thruster performance degradation due to fuel flow loss from multiple thruster usages. Second, new techniques for solving linear programming problems with uncertain data are explored. In particular, a robust LP (RLP) formulation is developed here to deal with uncertainty in either the thruster performance or the velocity and positional measurements. The estimation process is a combination of a Kalman filter and a Generalized Likelihood Ratio (GLR) test for actuator fault detection. A new model-comparison (MC) approach is introduced in conjunction with the GLR test to quickly and reliably determine the exact nature of the failure, once a malfunction has been detected. Finally, the simulations of the estimator and thrust mapper system are performed on the SPHERES and Orion formation flying test beds and results show improved control capabilities along with significant fuel saving. en_US
dc.description.statementofresponsibility by Trent Yang. en_US
dc.format.extent 147 p. en_US
dc.format.extent 6138189 bytes
dc.format.extent 6157302 bytes
dc.format.mimetype application/pdf
dc.format.mimetype application/pdf
dc.language.iso 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
dc.subject Aeronautics and Astronautics. en_US
dc.title Optimal thruster selection with robust estimation for formation flying applications 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 54402122 en_US


Files in this item

Name Size Format Description
54402122-MIT.pdf 8.519Mb PDF Full printable version

This item appears in the following Collection(s)

Show simple item record

MIT-Mirage