This paper describes a comprehensive study of vibration reduction in a four-bladed helicopter rotor using an actively controlled flap (ACF) located on the blade. This sequel to an earlier feasibility study examines the influence of using a more sophisticated fully flexible blade model on the potential of the ACF ror reducing vibrations. A deterministic feedback controller is implemented to reduce the 4/rev hub loads. Comparisons with the earlier study showed that the use of the more refined blade model results in a dramatic improvement in the vibration reduction effectiveness and power efficiency of the ACF, but at the cost of slightly higher input angles. Trend studies show that the torsional stiffness of the blade and the ACF spanwise location are important parameters. Finally, a time-domain simulation of the helicopter response to control is carried out to investigate the validity of the quasi static frequency domain approach to formulating control strategies. It was found that the quasi static assumption is equivalent to the requirement that sufficient time must be allowed between control updates for the transient vibrations to die out.
Vibration reduction in hingeless rotors using an actively controlled trailing edge flap: implementation and time domain simulation
Schwingungsverminderung bei scharnierlosen Rotoren mit einer aktiv geregelten Klappe: Aufbau und Simulation
1994
15 Seiten, 19 Bilder, 1 Tabelle, 37 Quellen
Conference paper
English
Aeroelastic Stability of Trailing-Edge Flap Helicopter Rotors
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