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dc.contributor.advisorWhitaker, H. Philip
dc.contributor.authorAnderson, Richard W.
dc.contributor.authorRoane, Donald P.
dc.date.accessioned2012-08-29T23:32:44Z
dc.date.available2012-08-29T23:32:44Z
dc.date.issued1960-05
dc.identifier.urihttp://hdl.handle.net/10945/12470
dc.description.abstractThe average burning rates of composite solid rocket propellant were measured in acceleration fields up to 2000 times the standard acceleration of gravity. The acceleration vector was perpendicular to and into the burning surface. Propellant strands were burned in a combustion bomb mounted on a centrifuge, and surge tanks were employed to ensure essentially constant pressure burning at 500, 1000, and 1500 psia. The burning rates of both aluminized and non-aluminized composite propellants were found to depend on acceleration. The effect of acceleration on burning rate was found to depend on the burning rate of the propellant without acceleration, aluminum mass loading, and aluminum mass median particle size. The relative burning rate increase was found to be greater for slow burning propellant than for faster burning propellants. The experimental results are compared to the analytical models proposed by Crowe for aluminized propellants and by Glick for non-aluminized propellants. The results indicate that these models do not adequately predict the observed relative burning rate increase with acceleration, and hence, that more complex modeling will be required to explain the observed acceleration effect.en_US
dc.description.abstract(Author)The system studied is a surface-to-air guided missile whose aerodynamic and control characteristics can be represented by a set of linear differential equations. The objects of the study are to select a set of control system gains which will give specified performance of the missile within the roll and yaw subsystems and at the same time to minimize the coupling effects whereby motion about one of the axes causes dynamic response about the other axis. The system is studied analytically using the mathematics of control system synthesis and design. Analytic investigations are paralleled by system simulation on a REAC analogue computer. Using the above methods, gains are selected which give specified response in the roll stabilization and yaw control subsystems and suitably damped response due to coupled motions between systems. The study also investigates the possibilities of compensation to attenuate or eliminate coupled response.en_US
dc.description.urihttp://archive.org/details/aninvestigationo1094512470
dc.language.isoen_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.lcshAeronauticsen_US
dc.titleAn investigation of the roll-yaw couplings in a surface-to-air guided missileen_US
dc.typeThesisen_US
dc.contributor.corporateCambridge, Massachusetts : Massachusetts Institute of Technology (MIT)
dc.contributor.departmentAeronautics and Astronautics
dc.description.serviceLieutenant Commander, United States Navyen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S.en_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.grantorCambridge, Massachusetts : Massachusetts Institute of Technology (MIT)en_US


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