An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability Page: 17 of 51
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NACA RM A56H30
limiter alone, and the required rudder servo deflection, at some flight
conditions tested, were reduced as much as 50 percent compared to those
of the sideslip limiter alone. Feedback characteristics for augmentation
schemes employing combination feedback quantities varied with flight con-
dition in a manner similar to the single feedback cases discussed above.
A combination roll-rate limiter and pq device (an augmentation
scheme using feedback proportional to :the product of rolling and pitching
velocity) was also investigated, with results very similar to the sideslip
limiter and roll-rate-limiter combination.
Ames Aeronautical Laboratory
National Advisory Committee for Aeronautics
Moffett Field, Calif., Aug. 30, 1956
REFERENCES
1. NACA High-Speed Flight Station: Flight Experience With Two High-Speed
Airplanes Having Violent Lateral-Longitudinal Coupling in Aileron
Rolls. NACA RM H55A13, 1955.
2. Wesesky, John L., and Stephens, Robert L.: Phase II Flight Tests of
the YF-102A Airplane, USAF S/N 53-1787. TR-55-31, Air Force Flight
Test Center, Edwards Air Force Base, Aug. 1955,.
3. Phillips, William H.:' Effect of Steady Rolling on Longitudinal and
Directional Stability. NACA TN 1627, 1948.
4. Abzug, M. J.: Kinematics and Dynamics of Fully-Maneuvering Airplanes.
Rep. ES-16144, Douglas Aircraft Co. Inc., El Segundo, June 15, 1955.
5. Gates, Ordway B., and Woodling, C. E.: A Theoretical Analysis of the
Effect of Engine Angular Momentum on Longitudinal and Directional
Stability in Steady Rolling Maneuvers. NACA RM L55G05, 1955.
6. Wolowicz, Chester H.: Time-Vector Determined Lateral Derivatives of
a Swept-Wing Fighter-Type Airplane With Three Different Vertical
Tails at Mach Numbers LBetween 0.70 and 1.48. NACA RM H56C20, 1956.
7. Drake, Hubert M., Finch, Thomas W., and Peele, James R.: Flight
Measurements of Directional Stability to a Mach Number of 1.48 for
an Airplane Tested With Three Different Vertical Tail Configurations.
NACA RM H55026, 1955.SrMi
16
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Creer, Brent Y. An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability, report, February 19, 1957; (https://digital.library.unt.edu/ark:/67531/metadc62909/m1/17/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.