International aerodynamic effects are a significant source of rotorcraft vibration, particularly in hover and in low-speed forward flight. Active control is proposed as a means for the reduction of the vibration induced by these interactional effects. A comprehensive rotorcraft analysis, including the effects of rotor-fuselage aerodynamic interactions, has been used to assess the feasibility of active rotor control for this application. It is shown that the vibratory forces on the rotor blades induced by interactional aerodynamic effects can be suppressed using active control methods. However, the pressure fluctuations on the fuselage surface that result from interactional effects are more difficult to suppress and require much stronger control inputs. Control inputs of the magnitude necessary to suppress the pressure fluctuations on the fuselage surface result in a significant load redistribution over the rotor disk and associated changes in rotor performance.
Active control of vibratory airloads induced by helicopter rotor-fuselage interactions
Aktive Regelung von Belastungen durch pulsierende Luft, hervorgerufen durch Rotor-Flugzeugrumpf Beeinflussungen an Hubschraubern
1993
8 Seiten, 11 Bilder, 30 Quellen
Conference paper
English
Validation of rotor vibratory airloads and application to helicopter response
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