Material characterization of Active Fiber Composite actuators for active twist helicopter rotor blade applications

2000 ◽  
Author(s):  
Viresh Wickramasinghe ◽  
Nesbitt Hagood
Keyword(s):  
Material Characterization ◽  
Rotor Blade ◽  
Fiber Composite ◽  
Helicopter Rotor ◽  
Active Fiber ◽  
Helicopter Rotor Blade ◽  
Active Twist ◽  
Active Fiber Composite

Parametric Study of Helicopter Blade for Active Twist Control Incorporating Macro Fiber Composite Actuator

2018 ◽  
Author(s):  
Mürüvvet Sinem Sicim ◽  
Dinçer Demirci ◽  
Metin Orhan Kaya
Keyword(s):  
Rotor Blade ◽  
Fiber Composite ◽  
Load Capacity ◽  
Thermal Strain ◽  
Helicopter Rotor ◽  
Design Parameters ◽  
Skin Thickness ◽  
Helicopter Rotor Blade ◽  
Active Twist ◽  
Macro Fiber Composite

Helicopters suffer from a number of problems raised from the high vibratory loads, noise generation, load capacity limitations, forward speed limitation etc. Especially unsteady aerodynamic conditions due to the different aerodynamic environment between advised and retreating side of the rotor cause most of these problems. Researchers study on passive and active methods to eliminate negative effects of aerodynamic loads. Nowadays, active methods such as Higher Harmonic Control (HHC), Individual Blade Control (IBC), Active Control of Structural Response (ACSR), Active Twist Blade (ATB), and Active Trailing-edge Flap (ATF) gain importance to vibration and noise reduction. In this paper, strain-induced blade twist control is studied integrated by Macro Fiber Composite (MFC) actuator. 3D model is presented to analyze the twisting of a morph and bimorph helicopter rotor blade comprising MFC actuator which is generally applied vibration suppression, shape control and health monitoring. The helicopter rotor blade is modeling with NACA23012 airfoil type and consists of D-spar made of unidirectional fiberglass, ±45° Glass Fiber Reinforced Polymer (GFRP) and foam core. Two-way fluid-structure interaction (FSI) method is used to simulate loop between fluid flow and physical structure to enable the behavior of the complex system. To develop piezoelectric effects, thermal strain analogy based on the similarities between thermal and piezo strains. The optimization results are obtained to show the influence of different design parameters such as web length, spar circular fitting, MFC chord length on active twist control. Also, skin thickness, spar thickness, web thickness are used to optimization parameters to illustrate effects on torsion angle by applying response surface methodology. Selection of correct design parameters can then be determined based on this system results.

Computational Material Characterization of Active Fiber Composite

2006 ◽  
Vol 18 (1) ◽  
pp. 19-28 ◽  
Author(s):  
Seung Hoon Paik ◽  
Tae Ho Yoon ◽  
Sang Joon Shin ◽  
Seung Jo Kim
Keyword(s):  
Material Characterization ◽  
Fiber Composite ◽  
Active Fiber ◽  
Computational Material ◽  
Active Fiber Composite

scholarly journals ACTIVE TWIST OF MODEL ROTOR BLADES WITH D-SPAR DESIGN

Transport ◽  
2007 ◽  
Vol 22 (1) ◽  
pp. 38-44 ◽  
Author(s):  
Andrejs Kovalovs ◽  
Evgeny Barkanov ◽  
Sergejs Gluhihs
Keyword(s):  
Finite Element ◽  
Finite Element Model ◽  
Rotor Blade ◽  
Element Model ◽  
Rotor Blades ◽  
Helicopter Rotor ◽  
3D Finite Element ◽  
3D Finite Element Model ◽  
Helicopter Rotor Blade ◽  
Active Twist

The design methodology based on the planning of experiments and response surface technique has been developed for an optimum placement of Macro Fiber Composite (MFC) actuators in the helicopter rotor blades. The baseline helicopter rotor blade consists of D‐spar made of UD GFRP, skin made of +450/‐450 GFRP, foam core, MFC actuators placement on the skin and balance weight. 3D finite element model of the rotor blade has been built by ANSYS, where the rotor blade skin and spar “moustaches” are modeled by the linear layered structural shell elements SHELL99, and the spar and foam ‐ by 3D 20‐node structural solid elements SOLID 186. The thermal analyses of 3D finite element model have been developed to investigate an active twist of the helicopter rotor blade. Strain analogy between piezoelectric strains and thermally induced strains is used to model piezoelectric effects. The optimisation results have been obtained for design solutions, connected with the application of active materials, and checked by the finite element calculations.

scholarly journals NUMERICAL OPTIMIZATION OF HELICOPTER ROTOR BLADE DESIGN FOR ACTIVE TWIST CONTROL

Aviation ◽  
2007 ◽  
Vol 11 (3) ◽  
pp. 3-9 ◽  
Author(s):  
Andrejs Kovalovs ◽  
Evgeny Barkanov ◽  
Sergejs Gluhihs
Keyword(s):  
Fatigue Life ◽  
Numerical Optimization ◽  
Rotor Blade ◽  
Operating Costs ◽  
Helicopter Rotor ◽  
Blade Design ◽  
Structural Components ◽  
Helicopter Rotor Blade ◽  
Active Twist ◽  
Different Sources

The vibration of a helicopter has several different sources, such as the rotor, engine and transmission system. This creates a number of problems with performance, for example poor manoeuvrability, discomfort of the pilot, low fatigue life of the structural components, and, consequently, high operating costs.

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