This paper investigates the aeroelastic stability of a smart helicopter rotor blade with trailing edge flaps. The coupled blade/flap/actuator equations were linearized by using small perturbation motions about a steady trimmed solution. Stability is then determined from an eigenanalysis of these homogeneous equations using a constant coefficient approximation approach and the Floquet method. The baseline correlation of stability calculations without trailing-edge flaps is carried out with wind tunnel test data and DART simulation for a typical 5-bladed bearingless rotor system. The correlation is good for both hover and forward flight conditions. Stability calculations for a rotor with trailing-edge flaps were conducted to examine the effect of flap aerodynamic balance and flap mass-balance. It is shown that both flap aerodynamic over-balancing and flap mass-unbalancing will have a destabilizing effect on the blade and flap system. The effect of rotor control system stiffness, blade torsion stiffness, actuator stiffness as well as flap mass on blade stability was studied. It is concluded that decreasing of either blade torsion stiffness or actuator stiffness will cause blade torsion-flap flutter problems. Increasing either rotor control system stiffness or flap mass would destabilize the blade/flap system.
Aeroelastic stability of smart trailing-edge flap helicopter rotors
2001
11 Seiten, 20 Quellen
Conference paper
English
Aeroelastic Stability of Trailing-Edge Flap Helicopter Rotors
Online Contents | 2003
|Aeroelastic stability of trailing-edge flap helicopter rotors
Tema Archive | 2003
|AIAA-2001-1675 Aeroelastic Stability of Smart Trailing-Edge Flap Helicopter Rotors
British Library Conference Proceedings | 2001
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