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dc.contributor.advisorCollins, Daniel J.
dc.contributor.advisorHoward, Rocjard M.
dc.contributor.authorGates, Russell J.
dc.dateSeptember 1995
dc.date.accessioned2012-08-22T15:33:42Z
dc.date.available2012-08-22T15:33:42Z
dc.date.issued1995-09
dc.identifier.urihttp://hdl.handle.net/10945/10806
dc.description.abstractParameter estimation is an inverse process in which stability derivatives are determined from time history flight data by matching the aircraft mathematical model's computed response with the measured response of the aircraft. Accurate parameter estimation depends mainly on instrumentation and input technique. Input technique is the focus of this thesis in which both classical inputs and optimal inputs were applied under the same flight conditions to the High Angle of Attack Research Vehicle (HARV) at NASA Dryden Flight Research Center. Post flight parameter estimation was conducted in all cases using a maximum likelihood technique to determine estimated of stability and control derivatives and their respective Cramer-Rao bounds. The Cramer-Rao bound is the most useful measure of estimate accuracy when comparing results from different input techniques assuming the same mathematical model and minimization technique were used for the parameter estimates. Comparison of the Cramer-Rao bounds showed that of the four input techniques used for determining parameter estimates, the Dryden single-surface input technique yielded the most accurate parameters for 75 percent of the estimates in all cases. Application of these conclusions in further research can save time and costs.en_US
dc.description.urihttp://archive.org/details/acomparisonoffli1094510806
dc.format.extentxiii, 103 p. : ill.en_US
dc.format.extent28 cm.en_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.subject.lcshAerodynamics.en_US
dc.titleA comparison of flight input techniques for parameter estimation of highly-augmented aircraften_US
dc.contributor.departmentAeronautical Engineering
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate School (U.S.)en_US


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