Reduction of vibrations due to dynamic stall in helicopters using an actively controlled flap

Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

Volumn 3, Issue , 2002, Pages 1826-1839

  Depailler, G ^a   Friedmann, P P ^a  

^a UNIVERSITY OF MICHIGAN   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMIC LOADS; ALGORITHMS; APPROXIMATION THEORY; COMPUTER SIMULATION; DRAG; VIBRATION CONTROL;

ACTIVE CONTROL;

HELICOPTERS;

EID: 0036078070     PISSN: 02734508     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.2514/6.2002-1431     Document Type: Conference Paper

References (27)

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5. Active flap control for vibration reduction and performance improvement
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10. Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor
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14. A semi-empirical model for dynamic stall
15. Small-scale rotor experiments with on-blade elevons to reduce blade vibratory loads in forward flight
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19. A hybrid periodic-shooting, autopilot method for rotorcraft trim analysis
20. Deceleration in the search for the global extremum of a function
21. Actuator saturation and its influence on vibration reduction by actively controlled flaps