Advanced guidance algorithms for the Ares V cargo launch vehicle

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Advanced guidance algorithms for the Ares V cargo launch vehicle

Please use this identifier to cite or link to this item: http://hdl.handle.net/10355/5648

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dc.contributor.advisor Wanta, Wayne en_US
dc.contributor.advisor Kluever, Craig A. (Craig Allan) en_US
dc.contributor.author Su, Shelly en_US
dc.date.accessioned 2010-02-23T17:13:22Z
dc.date.available 2010-02-23T17:13:22Z
dc.date.issued 2008 en_US
dc.date.submitted 2008 Summer en
dc.identifier.other SuH-071808-T11377 en_US
dc.identifier.uri http://hdl.handle.net/10355/5648
dc.description The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. en_US
dc.description Title from title screen of research.pdf file (viewed on August 17, 2009) en_US
dc.description Includes bibliographical references. en_US
dc.description Thesis (M.S.) University of Missouri-Columbia 2008. en_US
dc.description Dissertations, Academic -- University of Missouri--Columbia -- Mechanical and aerospace engineering. en_US
dc.description.abstract Launch ascent guidance is an area that routinely involves applications of optimization tools and optimal control theory. The vacuum ascent trajectory problem has been formulated as a two-point boundary-value problem with an interior-point state constraint and is solved with a method of direct parameter optimization. The direct method simplifies the more complicated full costate problem and an off-line trajectory optimization routine for the Ares V Cargo Launch Vehicle (CaLV) shows optimal performance as compared to trajectory simulations performed in the industry standard software, Optimal Trajectories by Implicit Simulation (OTIS). The guidance solution may also be determined through an analytic method, developed by assuming polynomial approximations for the steering profiles and flight-path angle profiles. The analytic solutions prove to be useful when applied to the Shuttle-based Powered Explicit Guidance (PEG) routine, where the results have been shown to converge to near a near optimal trajectory. en_US
dc.language.iso en_US en_US
dc.publisher University of Missouri--Columbia en_US
dc.relation.ispartof 2008 Freely available theses (MU) en_US
dc.subject.lcsh Launch vehicles (Astronautics) en_US
dc.subject.lcsh Boundary value problems en_US
dc.title Advanced guidance algorithms for the Ares V cargo launch vehicle en_US
dc.type Thesis en_US
thesis.degree.discipline Mechanical and aerospace engineering en_US
thesis.degree.grantor University of Missouri--Columbia en_US
thesis.degree.name M.S. en_US
thesis.degree.level Masters en_US
dc.identifier.merlin .b70641626 en_US
dc.identifier.oclc 430827822 en_US
dc.relation.ispartofcommunity University of Missouri-Columbia. Graduate School. Theses and Dissertations. Theses. 2008 Theses


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