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Pitch attitude stabilization system utilizing engine pressure ratio feedback signals
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1981 |
| Description | 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. |
| File Size | 470482 |
| Page Count | 7 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810017616 |
| Archival Resource Key | ark:/13960/t53f9kd0d |
| Language | English |
| Publisher Date | 1981-05-12 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Longitudinal Control Thrust Chamber Pressure Automatic Control Feedback Control Longitudinal Stability Pitch Inclination Aircraft Control Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
