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Pitch attitude stabilization system utilizing engine pressure ratio feedback signals

By W. W. Kelley

Abstract

The changes in the engine pressure ratio signals which result from thrust changes are used to generate a pitch stabilization signal. The signal is combined with other pitch control signals to automatically counteract pitching moments resulting from the changes in engine thrust

Topics: AIRCRAFT STABILITY AND CONTROL
Year: 1981
OAI identifier: oai:casi.ntrs.nasa.gov:19810017616

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