Gust alleviation concepts were studied numerically on a Boeing 707 aircraft with autopilot. Stochastic gust processes were studied in the frequency domain. The calculations show that the best solution is the control of the pitch position and the pitch velocity by using the autopilot mode pitch-hold. It is shown that additional control systems (e.g. transverse control) can substantially reduce disturbance. The influence of aircraft elasticity can only be assessed in a very simplified way. Deformations of airfoils and effects on stationary aerodynamics are determined.
Gust Alleviation Boenabminderung
1983
167 pages
Report
Keine Angabe
Englisch
Avionics , Aircraft , Automatic control , Flight stability tests , Gust alleviators , Gust loads , Automatic pilots , Boeing 707 aircraft , Computer programs , Deflectors , Elastic properties , Elevators (Control surfaces) , Longitudinal stability , Pitch (Inclination) , Turbulent flow , Foreign technology
NTRS | 1971
|SLUB | 1958
|Gust Alleviation Using Direct Gust Measurement
NTRS | 2000
|Gust Alleviation Using Direct Gust Measurement
NTIS | 2000
|Launch booster gust alleviation
AIAA | 1966
|