dc.contributor.advisor | Kluever, Craig A. (Craig Allan) | eng |
dc.contributor.author | Horneman, Kenneth R., 1968- | eng |
dc.date.issued | 2010 | eng |
dc.date.submitted | 2010 Summer | eng |
dc.description | The entire thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file; a non-technical public abstract appears in the public.pdf file. | eng |
dc.description | Title from PDF of title page (University of Missouri--Columbia, viewed on October 26, 2011). | eng |
dc.description | Thesis advisor: Dr. Craig Kluever. | eng |
dc.description | Vita. | eng |
dc.description | Ph. D. University of Missouri--Columbia 2010. | eng |
dc.description.abstract | Much effort has been put into developing technologies for next generation re-usable launch vehicles. Fully re-usable launch vehicles include a booster stage that is designed to land, usually near the launch site, after it has released the upper-stage, which continues to orbit. The fuel reserve needed to turn the booster stage around will usually be minimal For this reason, once the booster stage has completed a rocket-back maneuver, it will typically be at a high altitude (exo-atmospheric) but with low kinetic energy and a steep flight path angle on re-entry. Traditional re-entry guidance is designed for vehicles with a high velocity, and shallow flight path angle, and thus these traditional approaches are not appropriate for a low energy re-entry (LOER). The current research presents a set of guidance algorithms that will successfully guide a vehicle to landing starting from LOER condition. The guidance algorithms are designed to ensure the vehicle can achieve near optimal range performance when required and also to execute a sharp pull-up maneuver that balances the load factor constraint against the need to pull-up quickly before the dynamic pressure constraint is exceeded. The guidance approach has been tested for a wide variety of vehicles and mission scenarios, including more traditional initial conditions that would occur at the end of a High Energy Re-entry (HIER) from orbit. Thus, the guidance approach we have developed can be used as a more robust version of Terminal Area Energy Management (TAEM) guidance, as well as for LOER and has been tested for a wide range of vehicles, including the Space Shuttle and vehicles with a wide variety of L/D capability. Significant development has also gone into the engineering considerations needed to implement the guidance algorithms on a real vehicle. Program execution time, application of vehicle constraints, trajectory repeatability and other factors are all addressed in order to meet this need. | eng |
dc.description.bibref | Includes bibliographical references. | eng |
dc.format.extent | x, 129 pages | eng |
dc.identifier.oclc | 872561765 | eng |
dc.identifier.uri | https://hdl.handle.net/10355/12007 | |
dc.identifier.uri | https://doi.org/10.32469/10355/12007 | eng |
dc.language | English | eng |
dc.publisher | University of Missouri--Columbia | eng |
dc.relation.ispartofcommunity | University of Missouri--Columbia. Graduate School. Theses and Dissertations | eng |
dc.rights | OpenAccess. | eng |
dc.rights.license | This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivs 3.0 License. | |
dc.subject.lcsh | Launch vehicles (Astronautics) -- Trajectories | eng |
dc.subject.lcsh | Launch vehicles (Astronautics) -- Guidance systems | eng |
dc.subject.lcsh | Reusable space vehicles | eng |
dc.title | Automated trajectory generation and guidance for a new launch vehicle flight phases | eng |
dc.type | Thesis | eng |
thesis.degree.discipline | Mechanical and aerospace engineering (MU) | eng |
thesis.degree.grantor | University of Missouri--Columbia | eng |
thesis.degree.level | Doctoral | eng |
thesis.degree.name | Ph. D. | eng |