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dc.contributor.authorRang, Edward R.
dc.date.accessioned2013-01-23T21:56:07Z
dc.date.available2013-01-23T21:56:07Z
dc.date.issued1969-06-04
dc.identifier.urihttps://hdl.handle.net/10945/26106
dc.description.abstractA sum of normal acceleration and pitch rate appears to be the best variable to use to control aircraft in the longitudinal axis. The C*-Criterion specifies that the time response of this quantity called C* must fall in a prescribed envelope for all speeds and altitudes. It is equivalent to requiring the control system to hold the coefficients of a certain equation, which describes the aircraft's short-period motion, fixed. This is done by using feedbacks with variable gains. The gain-changing mechanism is found using gradient techniques. The system was shown to be practical by an analog simulation. It was found to be tolerant of instrument noise, elevator hysteresis, and other complications not accounted in the analytical derivations. The study strongly suggests a modification of the C*-Criterion. It is proposed that the coefficients in the expression of the quantity C* should be representative of the aircraft's parameters rather than have the values currently in use. (Author)en_US
dc.description.urihttp://archive.org/details/nonvaryingccontr00rang
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.lcshMETEOROLOGICAL SATELLITES.en_US
dc.titleA nonvarying-C* control scheme for aircraften_US
dc.typeTechnical Reporten_US
dc.identifier.npsreportNPS57RJ9061A


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