NASA NTRS · 19810017616
Pitch attitude stabilization system utilizing engine pressure ratio feedback signals
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.
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Kelley, W. W.. 1981-05-12. Pitch attitude stabilization system utilizing engine pressure ratio feedback signals. https://ntrs.nasa.gov/citations/19810017616
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