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Analysis of rotorcraft ground resonance with generic inter-blade damper configurations
Full text linkThe paper investigates the effect of inter-blade dampers with generic in-plane and out-of-plane attachment offsets on ground resonance stability proneness. An analytical formulation, considering dampers with radial offsets only is initially proposed. Sensitivity analyses show that the increase of radial offset reduces the cyclic lead-lag damping and stiffness, providing a non-zero contribution to collective terms. The analytical formulation is suitable, in a preliminary design phase, to define the optimal location of the inter-blade attachment points to avoid ground resonance phenomena and to stabilize the engine drive-train dynamics. A more detailed numerical approach is then presented to consider generic in-plane and out-of-plane attachment offsets. Ground resonance stability analyses are performed also for cases with dissimilar dampers. It is found that out-of-plane offset leads to a modification on the blade pitch-lag coupling, acting on the helicopter stability margins. However, to capture these effects it is necessary to include the overall blade motions, considering flap, lag, and pitch dynamics, together with the corresponding generalized aerodynamics forces, usually neglected in classical ground resonance analysis. Finally, the periodic stability with one damper inoperative shows how, with the radial offsets, the hybridized lead-lag collective and cyclic modes may fall into resonance conditions due to super-harmonics
Gust and Inflow Model Identification from Wind Tunnel Tests for Rotorcraft-Obstacle Interaction
Full text linkEvaluation of Steady and Periodic Trim Loads in Tiltrotors Using Multibody - Mid-Fidelity Aerodynamic Simulations
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Development of Innovative Movable Surfaces for the Next-Generation Civil Tiltrotor Aircraft
Full text linkA Comprehensive Aeroservoelastic Approach to Detect and Prevent Rotorcraft-Pilot Coupling Phenomena in Tiltrotors
No full textThis work investigates rotorcraft-pilot coupling phenomena in tiltrotors. A detailed tiltrotor model, representative of the Bell-Boeing XV-15, has been built. Biomechanical models of the pilot, acting on the power lever and on the centre stick, are included in feedback loop to define the Pilot-Vehicle System. Pilot-Assisted Oscillation phenomena are investigated on the overall conversion corridor using Nyquist's criterion. Pilot-in-the-loop analyses demonstrate that a critical parameter is detected in the vertical fins geometry. Due to an asymmetric flaperons deflection the wing's wake impacts on the vertical fins, producing a side force. The pulsating tail-side-force makes the fuselage to yaw and excites the asymmetric wing chord mode coupled with the lateral pilot's biomechanics, leading to a reduction, or even a loss, of stability. No unstable event is detected about the longitudinal direction. Conversely, a resonance between the pilot's biomechanics and the aircraft poorly damped symmetric wing bending mode is predicted about the vertical axis. The instability is found on the whole conversion corridor, although the source of excitation changes with reference to the nacelle angle. Means of prevention are implemented and discussed
Assessment of a Highly Parameterized Steady-State Microscale Wind Simulator for Urban Air Mobility Applications
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