Aeroelastic Response of Composite Helicopter Rotor with Random Material Properties

Murugan, Senthil; Ganguli, Ranjan; Harursampath, Dineshkumar

doi:10.2514/1.30180

Cited by 64 publications

(29 citation statements)

References 39 publications

(50 reference statements)

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“…The tested specimen (a curved daggerboard from the NACRA F20 Carbon catamaran) allows the DIC methodology to be assessed in challenging conditions due to its complex geometry and the fact that only small deformations are expected under aerodynamic loading. The presented methodology will be of use not only to high performance foils for catamarans, but also to wind turbine blades (Lin and Lai 2010, Fedorov, et al 2009, Karaolis, Musgrove and Jenimidis 1988, Nicholls-Lee, Boyd and Turnock 2009, helicopter rotors Chopre November-December, 1995, Murugan, Ganguli andHarursampath January-February, 2008), propeller blades (Khan, et al 2000, Lee and, ship rudders Wright 2000, Molland andTurnock 2007) and high performance racing cars (Thuwis, et al 2010). At the time of writing, little research has been developed involving Digital Image Correlation (DIC) within a wind tunnel to evaluate a coupled FSI problem.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Digital Image Correlation as a method of obtaining deformations of a structure under fluid load

Banks

Giovannetti

Soubeyran

et al. 2015

Journal of Fluids and Structures

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Digital Image Correlation (DIC) is employed for the measurement of full-field deformation during fluid-structure interaction experiments in a wind tunnel. The methodology developed for the wind tunnel environment is quantitatively assessed. The static deformation error of the system is shown to be less than 0.8% when applied to a curved aerofoil specimen moved through known displacements using a micrometer. Enclosed camera fairings were shown to be required to minimise error due to wind induced camera vibration under aerodynamic loading. The methodology was demonstrated using a high performance curved foil, from a NACRA F20 sailing catamaran, tested within the University of Southampton RJ Mitchell, 3.5m x 2.4m, wind tunnel. The aerodynamic forces induced in the wind tunnel are relatively small, compared with typical hydrodynamic loading, resulting in small deformations. The coupled deflection and blade twist is evaluated over the tip region (80-100% Span, measured from the root) for a range of wind speeds and angles of attack. Steady deformations at low angles of attack were shown to be well captured however unsteady deformations at higher angles of attack were observed as an increase in variability due to hardware limitations in the current DIC system. It is concluded that higher DIC sample rates are required to assess unsteady deformations in the future. The full field deformation data reveals limited blade twist for low angles of attack, below the stall angle. For larger angles, however, there is a tendency to reduce the effective angle of attack at the tip of the structure, combined with an unsteady structural response. This capability highlights the benefits of the presented methodology over fixed-point measurements as the three dimensional foil deflections can be assessed over a large tip region. In addition, the methodology demonstrates that very small deformations and twist angles can be resolved.

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Section: Introductionmentioning

confidence: 99%

Assessment of Digital Image Correlation as a method of obtaining deformations of a structure under fluid load

Banks

Giovannetti

Soubeyran

et al. 2015

Journal of Fluids and Structures

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“…Considering composite multilayered fibrous composites it is possible to investigate three different categories of 2D composite constructions: Pettit [20] pointed out that uncertainty (imprecision) should be taken into account in the case of too conservative, inefficient designs or due to adoption of new technologies and techniques. Modelling of aeroelastic characteristics with uncertain elastic moduli and Poisson's ratio was introduced by Murugan et al [39,40]. Liaw [41], Manan, Cooper [42], Scarth et al [43] estimated the flutter speed of a composite plate with uncertainty in the ply orientations, thickness, elastic moduli, and material and air densities.…”

Section: Composite Materialsmentioning

confidence: 99%

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

2019

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Aeroelastic optimization has become an indispensable component in the evaluation of divergence and flutter characteristics for plated/shell structures. The present paper intends to review the fundamental trends and dominant approaches in the optimal design of engineering constructions. A special attention is focused on the formulation of objective functions/functional and the definition of physical (material) variables, particularly in view of composite materials understood in the broader sense as not only multilayered laminates but also as sandwich structures, nanocomposites, functionally graded materials, and materials with piezoelectric actuators/sensors. Moreover, various original aspects of optimization problems of composite structures are demonstrated, discussed, and reviewed in depth.

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“…Monte Carlo Simulation (MCS) is a commonly used technique, and was used by Murugan et al (2008) to model the aeroelastic response of a composite rotor blade with uncertain elastic moduli and Poisson's ratio. Monte Carlo Simulation can be computationally expensive due to the large number of model runs required, and as such, it is common to use surrogate models in order to reduce the computation time.…”

Section: Introductionmentioning

confidence: 99%

Reliability-based aeroelastic design of composite plate wings using a stability margin

Scarth

Cooper

2017

Struct Multidisc Optim

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Reliability-based design is concerned with ensuring that constraints are enforced with acceptable probability under inherent variability in properties. In aircraft design, such a constraint may be that aeroelastic instability does not occur at velocities encountered by the aircraft. This approach can be complicated, as the aeroelastic instability speed is a discontinuous function of material properties, on account of particular modes only becoming unstable for some parameter values. In reliability analysis, it is common to use surrogate models due to the computational expense associated with Monte Carlo Simulation, however, such methods can be inaccurate when emulating discontinuous functions such as the aeroelastic instability speed. In this paper, an alternative approach is proposed in which Gaussian process surrogate models are fitted directly to each of the modal eigenvalues at the design air-speed, and used to emulate a stability margin based upon the most critical eigenvalue. Using this approach, it is shown that the reliability may be estimated for the aeroelastic stability using smooth emulators, thereby overcoming the problems associated with discontinuities. The method is demonstrated for layup optimisation of composite plate wings with uncertain ply angles, in which the probability of aeroelastic instability occurring is minimised for a prescribed air-speed. In uncertainty quantification, a good agreement is found with Monte Carlo Simulation with an order of two magnitudes reduction in model runs. Through reliability-based design, reductions in the probability of failure of up to 99.8% are achieved by increasing the stability margin at the design speed.

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Aeroelastic Response of Composite Helicopter Rotor with Random Material Properties

Cited by 64 publications

References 39 publications

Assessment of Digital Image Correlation as a method of obtaining deformations of a structure under fluid load

Assessment of Digital Image Correlation as a method of obtaining deformations of a structure under fluid load

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

Reliability-based aeroelastic design of composite plate wings using a stability margin

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