Advanced Search
DSpace@MIT

A Legendre Pseudospectral Method for rapid optimization of launch vehicle trajectories

Research and Teaching Output of the MIT Community

Show simple item record

dc.contributor.advisor I. Michael Ross, Richard E. Phillips and John J. Deyst. en_US
dc.contributor.author Rea, Jeremy Ryan, 1975- en_US
dc.contributor.other Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. en_US
dc.date.accessioned 2005-08-23T21:40:48Z
dc.date.available 2005-08-23T21:40:48Z
dc.date.copyright 2001 en_US
dc.date.issued 2001 en_US
dc.identifier.uri http://hdl.handle.net/1721.1/8608
dc.description Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001. en_US
dc.description Includes bibliographical references (p. 259-261). en_US
dc.description.abstract A Legendre Pseudospectral Method for launch vehicle trajectory optimization, pro­ posed by Mike Ross and Fariba Fahroo of the Naval Postgraduate School, is presented and applied successfully to several launch problems. The method uses a Legendre pseudospectral differentiation matrix to discretize nonlinear differential equations (such as the equations of motion) into nonlinear algebraic equations. The equations are then posed in the form of a nonlinear optimization problem and solved numerically. The method is demonstrated to work very well with both continuous and discontinuous states and controls. The method is applied to the following launch problems: the single-stage and two-stage Goddard problem; a simplified, single-stage, two-dimensional launch problem; and a two-stage, three-dimensional launch problem. A technique for reducing the size of problems with second order differential equations is presented and applied. This technique is shown to increase the speed of convergence of some problems. A predictive guidance algorithm demonstrates the feasibility of using the method to find both open- and closed-loop controls for a single-stage, three dimensional launch problem. The effects of different aerodynamic models between the optimizer and the "real" simulation are briefly analyzed. A number of issues that need to be resolved before the algorithm can be used in-flight for closed-loop guidance are described en_US
dc.description.statementofresponsibility by Jeremy Ryan Rea. en_US
dc.format.extent 261 p. en_US
dc.format.extent 12933158 bytes
dc.format.extent 12932909 bytes
dc.format.mimetype application/pdf
dc.format.mimetype application/pdf
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
dc.subject Aeronautics and Astronautics. en_US
dc.title A Legendre Pseudospectral Method for rapid optimization of launch vehicle trajectories 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 49341903 en_US


Files in this item

Name Size Format Description
49341903-MIT.pdf 12.33Mb PDF Full printable version

This item appears in the following Collection(s)

Show simple item record

MIT-Mirage