Optimizing tuning masses for helicopter rotor blade vibration reduction and comparison with test data

1993 ◽  
Vol 30 (6) ◽  
pp. 906-910 ◽  
Author(s):  
Jocelyn I. Pritchard ◽  
Howard M. Adelman ◽  
Joanne L. Walsh ◽  
Matthew L. Wilbur
Keyword(s):  
Test Data ◽  
Rotor Blade ◽  
Vibration Reduction ◽  
Helicopter Rotor ◽  
Blade Vibration ◽  
Helicopter Rotor Blade

scholarly journals Multiple-Surrogate Approach to Helicopter Rotor Blade Vibration Reduction

AIAA Journal ◽  
2009 ◽  
Vol 47 (1) ◽  
pp. 271-282 ◽  
Author(s):  
Bryan Glaz ◽  
Tushar Goel ◽  
Li Liu ◽  
Peretz P. Friedmann ◽  
Raphael T. Haftka
Keyword(s):  
Rotor Blade ◽  
Vibration Reduction ◽  
Helicopter Rotor ◽  
Blade Vibration ◽  
Helicopter Rotor Blade

H ∞ Control of Smart Structure Helicopter Rotor Blade

1991 ◽  
Author(s):  
R. Kashani ◽  
S. Melkote ◽  
A. Sorgenfrei
Keyword(s):  
Rotor Blade ◽  
Active Vibration Control ◽  
Region Of Interest ◽  
Smart Structure ◽  
Helicopter Rotor ◽  
Appreciable Amount ◽  
Modelling Uncertainty ◽  
Helicopter Rotor Blade ◽  
Active Vibration ◽  
Bending Modes

Abstract Active vibration control of helicopter rotor blade is studied. For the purpose of illustration, we have considered only flap wise vibration of a hingeless rotor blade, and modelled it, using finite element method, by 20 beam elements. The first 12 bending modes of the system are considered in the model. A H∞ controller is designed for the plant formulated as above. The result of the numerical simulation of the closed-loop system shows that the control introduces an appreciable amount of damping in the frequency region of interest. The consideration of the modelling uncertainty in the synthesis of the controller resulted in a design which is robust stable in presence of formulated model uncertainty.

An Investigation of the Aerodynamic and Vibration Behavior of a Helicopter Rotor Blade

2020 ◽  
Author(s):  
Mohammad Khairul Habib Pulok ◽  
Uttam K. Chakravarty
Keyword(s):  
Rotor Blade ◽  
Fluid Structure Interaction ◽  
Interaction Model ◽  
Scale Model ◽  
Helicopter Rotor ◽  
Small Scale ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Aerodynamic Analysis ◽  
Helicopter Rotor Blade

Abstract Rotary-wing aircrafts are the best-suited option in many cases for its vertical take-off and landing capacity, especially in any congested area, where a fixed-wing aircraft cannot perform. Rotor aerodynamic loading is the major reason behind helicopter vibration, therefore, determining the aerodynamic loadings are important. Coupling among aerodynamics and structural dynamics is involved in rotor blade design where the unsteady aerodynamic analysis is also imperative. In this study, a Bo 105 helicopter rotor blade is considered for computational aerodynamic analysis. A fluid-structure interaction model of the rotor blade with surrounding air is considered where the finite element model of the blade is coupled with the computational fluid dynamics model of the surrounding air. Aerodynamic coefficients, velocity profiles, and pressure profiles are analyzed from the fluid-structure interaction model. The resonance frequencies and mode shapes are also obtained by the computational method. A small-scale model of the rotor blade is manufactured, and experimental analysis of similar contemplation is conducted for the validation of the numerical results. Wind tunnel and vibration testing arrangements are used for the experimental validation of the aerodynamic and vibration characteristics by the small-scale rotor blade. The computational results show that the aerodynamic properties of the rotor blade vary with the change of angle of attack and natural frequency changes with mode number.

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