Terfenol-D-driven flaps for helicopter vibration reduction

1993 ◽  
Author(s):  
Ralph C. Fenn ◽  
James R. Downer ◽  
Dariusz A. Bushko ◽  
Vijay Gondhalekar ◽  
Norman D. Ham
Keyword(s):  
Vibration Reduction ◽  
Helicopter Vibration

Terfenol-D driven flaps for helicopter vibration reduction

1996 ◽  
Vol 5 (1) ◽  
pp. 49-57 ◽  
Author(s):  
Ralph C Fenn ◽  
James R Downer ◽  
Dariusz A Bushko ◽  
Vijay Gondhalekar ◽  
Norman D Ham
Keyword(s):  
Vibration Reduction ◽  
Helicopter Vibration

Helicopter Vibration Reduction Using Discrete Controllable-Stiffness Devices at the Rotor Hub

2002 ◽  
Vol 39 (4) ◽  
pp. 668-677 ◽  
Author(s):  
Farhan Gandhi ◽  
Phuriwat Anusonti-Inthra
Keyword(s):  
Vibration Reduction ◽  
Helicopter Vibration

Surrogate based design optimisation of composite aerofoil cross-section for helicopter vibration reduction

2012 ◽  
Vol 116 (1181) ◽  
pp. 709-725 ◽  
Author(s):  
M. S. Murugan ◽  
R. Ganguli ◽  
D. Harursampath
Keyword(s):  
Objective Function ◽  
Cross Section ◽  
Rotor Blade ◽  
Vibration Reduction ◽  
Substantial Reduction ◽  
Response Surfaces ◽  
Design Optimisation ◽  
Baseline Design ◽  
Real Coded Genetic Algorithm ◽  
Helicopter Vibration

AbstractDesign optimisation of a helicopter rotor blade is performed. The objective is to reduce helicopter vibration and constraints are put on frequencies and aeroelastic stability. The ply angles of the D-spar and skin of the composite rotor blade with NACA 0015 aerofoil section are considered as design variables. Polynomial response surfaces and space filling experimental designs are used to generate surrogate models of the objective function with respect to cross-section properties. The stacking sequence corresponding to the optimal cross-section is found using a real-coded genetic algorithm. Ply angle discretisation of 1°, 15°, 30° and 45° are used. The mean value of the objective function is used to find the optimal blade designs and the resulting designs are tested for variance. The optimal designs show a vibration reduction of 26% to 33% from the baseline design. A substantial reduction in vibration and an aeroelastically stable blade is obtained even after accounting for composite material uncertainty.

Helicopter Vibration Reduction by Local Structural Modification

1982 ◽  
Vol 27 (3) ◽  
pp. 43-47
Author(s):  
B. P. Wang ◽  
L. Kitis ◽  
W. D. Pilkey ◽  
A. B. Palazzolo
Keyword(s):  
Structural Modification ◽  
Vibration Reduction ◽  
Helicopter Vibration
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