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Based on blade element/momentum theory the aerodynamic impact on rotor controls and blade flapping caused by a straight line vortex penetrating orthogonally the plane of a rotor disk is solved… Click to show full abstract
Based on blade element/momentum theory the aerodynamic impact on rotor controls and blade flapping caused by a straight line vortex penetrating orthogonally the plane of a rotor disk is solved using a realistic swirl velocity profile. The collective and cyclic controls needed for disturbance rejection and the coning and cyclic flapping motion developing are computed.
Keywords:
controls blade;
rotor controls;
rotor;
flapping caused;
blade flapping;
disturbance
Journal Title: Journal of The American Helicopter Society
Year Published: 2018
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Journal Title: Journal of The American Helicopter Society
Year Published: 2018
Link to full text (if available)
Share on Social Media: Sign Up to like & get
recommendations!