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dc.contributor.advisorWhitmore, Stephen A.
dc.contributor.authorSchafer, Michael D.
dc.date.accessioned2012-03-14T17:42:13Z
dc.date.available2012-03-14T17:42:13Z
dc.date.issued2002-09
dc.identifier.urihttp://hdl.handle.net/10945/4536
dc.description.abstractThe single largest contributor to the cost of putting objects into space is that of the launch portion. The currently available chemical rockets are only capable of specific impulse (Isp) values on the average of 300-350 seconds, with a maximum of 450 seconds. In order to improve the performance of the current families of launch vehicles, it is necessary to increase the performance of the rocket motors, and conversely the amount of propellant/oxidizer carried. The purpose of this thesis was to determine the feasibility of employing SCRAMJET technology for an intermediate propulsive stage of an expendable launch vehicle. This was motivated by the fact that SCRAMJETS offer a very high propulsive efficiency when compared to conventional chemical rockets. The incorporation of a SCRAMJET engine into the configuration "stack" of an expendable launch vehicle, offers the promise of increased payload mass fraction or an increase in the number of attainable orbital profiles. Analytical tools were developed using open-source software to identify launch trajectories for the SCRAMJET-enabled rocket configurations, and to determine how these would differ from conventional launch profiles. The effects of incremental increases in configuration lift and drag coefficients due to the SCRAMJET stage was analyzed. It was determined that incorporation of SCRAMJET Technology into an expendable rocket configuration offered marked improvement in performance, reduction in total launch weight, and increase operational flexibility when compared to a similarly sized conventional chemical rocket.en_US
dc.description.urihttp://archive.org/details/feasibilityofscr109454536
dc.format.extentxxii, 95 p. : col. ill. ;en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshLaunch vehicles (Astronautics)en_US
dc.subject.lcshRockets (Aeronautics)en_US
dc.titleFeasibility of SCRAMJET technology for an intermediate propulsive stage of an expendable launch vehicleen_US
dc.typeThesisen_US
dc.contributor.schoolRacoosin, Charles M..
dc.contributor.departmentSpace Systems Academic Group
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Space Systems Operationsen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineSpace Systems Operationsen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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