NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Pitch attitude stabilization system utilizing engine pressure ratio feedback signalsThe 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.
Document ID
19810017616
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Kelley, W. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
May 12, 1981
Subject Category
Aircraft Stability And Control
Report/Patent Number
Patent Number: US-PATENT-4,266,743
Patent Number: NASA-CASE-LAR-12562-1
Patent Application Number: US-PATENT-APPL-SN-015995
Accession Number
81N26152
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,266,743|NASA-CASE-LAR-12562-1
Patent Application
US-PATENT-APPL-SN-015995

Related Records

IDRelationTitleN79-20135Superseded By
No Preview Available