The effects of aeroelasticity on stability and control are discussed under the two general categories of longitudinal and lateral motion. In each case the effects of wing, fuselage, and tail flexibility on stability of motion and effectiveness of control are discussed for various flight conditions including dynamic pressure and Mach number. First, review is given of the various pertinent problems, such as reduced roll damping and aileron reversal, and the extent to which they appear in recent designs of each of the several classes of airplanes (fighters, bombers, transports). Second, some features which have been incorporated in recent designs for the purpose of reducing adverse aeroelastic effects on stability and control are discussed. Third, brief descriptions of some current analytical and experimental techniques for the study of aeroelastic problems associated with the present subject are given. Finally, an indication is given of new problems which may arise as a consequence of trends in high-speed airplane configurations. Results from studies of a supersonic transport airplane and of a winged missile are included. (Author)
Effects of Aeroelasticity on the Stability and Control Characteristics of Airplanes
1961
37 pages
Report
Keine Angabe
Englisch
Aircraft , Airplanes , Aeroelasticity , Stability , Control , Pitch(Motion) , Roll , Fuselages
Effects of aeroelasticity on stability and control characteristics of airplanes
Engineering Index Backfile | 1961
|Aeroelasticity in Stability and Control
NTIS | 1957
FLIGHT VEHICLE AEROELASTICITY - Nonlinear Aeroelasticity
Online Contents | 2003
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