NDLI: Optimization of Vibration Reduction in a Helicopter Blade With 2 Way Fluid-Structure Interaction

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Optimization of Vibration Reduction in a Helicopter Blade With 2 Way Fluid-Structure Interaction

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Sicim, Mürüvvet Sinem Kaya, Metin Orhan
Copyright Year	2018
Abstract	The main goal of this study is the optimization of vibration reduction on helicopter blade by using macro fiber composite (MFC) actuator under pressure loading. Due to unsteady aerodynamic conditions, vibration occurs mainly on the rotor blade during forward flight and hover. High level of vibration effects fatigue life of components, flight envelope, pleasant for passengers and crew. In this study, the vibration reduction phenomenon on helicopter blade is investigated. 3D helicopter blade model is used to perform the aeroelastic behavior of a helicopter blade. Blade design is created by Spaceclaim and finite element analysis is conducted by ANSYS 19.0. Generated model are solved via Fluent by using two-way fluid-solid coupling analysis, then the analyzed results (all aerodynamic loads) are directly transferred to the structural model. Mechanical results (displacement etc.) are also handed over to the Fluent analysis by helping fluid-structure interaction interface. Modal and harmonic analysis are performed after FSI analysis. Shark 120 unmanned helicopter blade model is used with NACA 23012 airfoil. The baseline of the blade structure consists of D spar made of unidirectional Glass Fiber Reinforced Polymer +45°/−45° GFRP skin. MFC, which was developed by NASA’s Langley Research Center for the shaping of aerospace structures, is applied on both upper and lower surfaces of the blade to reduce the amplitude in the twist mode resonant frequency. D33 effect is important for elongation and to observe twist motion. To foresee the behavior of the MFC, thermo-elasticity analogy approach is applied to the model. Therefore, piezoelectric voltage actuation is applied as a temperature change on ANSYS. The thermal analogy is validated by using static behavior of cantilever beam with distributed induced strain actuators. Results for cantilever beam are compared to experimental results and ADINA code results existing in the literature. The effects of fiber orientation of MFC actuator and applied voltage on vibration reduction on helicopter blade are represented. The study shows that torsion mode determines the optimum placement of actuators. Fiber orientation of the MFC has few and limited influences on results. Additionally, the voltage applied on MFC has strong effects on the results and they must be selected according to applied model.
Sponsorship	Aerospace Division
File Format	PDF
ISBN	9780791851944
DOI	10.1115/SMASIS2018-8017
Volume Number	Volume 1: Development and Characterization of Multifunctional Materials; Modeling, Simulation, and Control of Adaptive Systems; Integrated System Design and Implementation
Conference Proceedings	ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems
Language	English
Publisher Date	2018-09-10
Publisher Place	San Antonio, Texas, USA
Access Restriction	Subscribed
Subject Keyword	Actuators Temperature Blades Flight Fluid structure interaction Optimization Aerospace industry Fibers Glass fibers Design Fluids Polymers Torsion Elongation Fatigue life Vibration Rotors Airfoils Glass reinforced plastics Cantilever beams Pressure Displacement Spar platforms Stress Composite materials Thermoelasticity Resonance Skin Finite element analysis Wing spars
Content Type	Text
Resource Type	Article

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