Fluid/structure interaction in numerical aeroelastic simulation

Zwaan, R.J.; Prananta, B.B.

doi:10.1016/s0020-7462(01)00110-x

Cited by 19 publications

(7 citation statements)

References 22 publications

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“…The method is readily implemented with reduced computational time, given that no sub-cycling within each timestep is required to ensure conservation and compatibility condition as required of the two-way method. The uncoupled method allows the use of separate solvers without the need in formulating an interface/coupling algorithm to couple the independent codes, [6]. As a first step in this method, an initial 3D flow field analysis is performed to establish the unsteady forcing which is utilized as boundary condition in the finite element code to predict the unsteady stresses and subsequent fatigue life estimation.…”

Section: ) Fluid-structure Interaction Modellingmentioning

confidence: 99%

Application of Spectral Method for Vibration-Induced High-Cycle Fatigue Evaluation of an HP Turbine Blade

Ubulom

2020

Volume 10B: Structures and Dynamics

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A method of fluid-structure interaction coupling is implemented for a forced-response, vibration-induced fatigue life estimation of a high-pressure turbine blade. Two simulations approaches; a two-way (fully-coupled) and one-way (uncoupled) methods are implemented to investigate the influence of fluidsolid coupling on a turbine blade structural response. The fatigue analysis is performed using the frequency domain spectral moments estimated from the response power spectral density of the two simulation cases. The method is demonstrated in light of the time-domain method of the rainflow cycle counting method with mean stress correction. Correspondingly, the mean stress and multiaxiality effects are also accounted for in the frequency domain spectral approach. In the mean stress case, a multiplication coefficient is derived based on the Morrow equation, while the case of multiaxiality is based on a criterion which reduces the triaxial stress state to an equivalent uniaxial stress using the critical plane assumption. The analyses show that while the vibration-induced stress histories of both simulation approaches are stationary, they violate the assumption of normality of the frequency domain approaches. The stress history profile of both processes can be described as platykurtic with the distributions having less mass near its mean and in the tail region, as compared to a Gaussian distribution with an equal standard deviation. The fully-coupled method is right leaning with positive skewness while the uncoupled approach is left leaning with negative skewness. The directional orientation of the principal axes was also analyzed based on the Euler angle estimation. Although noticeable differences were found in the peak distribution of the normal stresses for both methods, the predicted Euler angle orientations were consistent in both cases, depicting a similar orientation of the critical plane during a crack initiation process. It is shown that the fatigue life estimation was conservative in the fully-coupled solution approach.

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Section: ) Fluid-structure Interaction Modellingmentioning

confidence: 99%

Application of Spectral Method for Vibration-Induced High-Cycle Fatigue Evaluation of an HP Turbine Blade

Ubulom

2020

Volume 10B: Structures and Dynamics

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“…This shortcoming may be addressed by employing a technique known as partitioned analysis procedure, in which a fully coupled set of field equations is decoupled into two or more partitions that are solved independently [20,40]. The partitions are executed incrementally in an alternating series and exchange data as the solution progresses in order to represent the effect of the coupling, an approach frequently employed in fluid-structure interaction problems [41][42][43], but applied here to a thermomechanical problem. For a thermomechanically coupled problem, the system in equations (3.3) and (3.9) is separated into thermal and structural partitions.…”

Section: Analysis Approachmentioning

confidence: 99%

Coupled behavior of shape memory alloy-based morphing spacecraft radiators: experimental assessment and analysis

Bertagne

Walgren

Erickson

et al. 2018

Smart Mater. Struct.

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Thermal control is an important aspect of spacecraft design, particularly in the case of crewed vehicles, which must maintain a precise internal temperature at all times in spite of significant variations in the external thermal environment and internal heat loads. Future missions beyond low Earth orbit will require radiator systems with high turndown ratios, defined as the ratio between the maximum and minimum heat rejection rates achievable by the radiator system. Current radiators are only able to achieve turndown ratios of 3:1, far less than the 12:1 turndown ratio requirement expected for future missions. An innovative morphing radiator concept uses the temperature-induced phase transformation of shape memory alloy (SMA) materials to achieve turndown ratios that are predicted to exceed 12:1 via substantial geometric reconfiguration. Developing mathematical and computational models of these morphing radiators is challenging due to the strong two-way thermomechanical coupling not present in traditional fixed-geometry radiators and not widely considered in the literature. Although existing simulation tools are capable of analyzing the behavior of some thermomechanically coupled structures, general problems involving radiation and deformation cannot be modeled using publicly available codes due to the complexity of modeling spatially evolving boundary fields. This paper provides important insight into the operational response of SMA-based morphing radiators by employing computational tools developed to overcome previous shortcomings. Several example problems are used to demonstrate the novel radiator concept. Additionally, a prototype morphing radiator was designed, fabricated, and tested in a thermal environment compatible with mission operations. An associated finite element model of the prototype was developed and executed. Model predictions of radiator performance generally agree with the experimental data, giving confidence that the tools developed are able to accurately represent the thermomechanical coupling present in morphing radiators and that such tools will be useful in future designs.

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“…23 In the field of aeroelasticity, for any flight vehicle, the states of motion are decided by the inertial force, damping force, elastic force and aerodynamic force, 24 as shown in equation (3) fF iner g + fF damp g + fF elas g = fF aero g ð 3Þ…”

Section: Fluid-structure Interactionmentioning

confidence: 99%

“…where [ M ] represents the structural mass matrix, [ C ] is the matrix of damping, [ K ] is the stiffness matrix and { F } is the vector of structure load. 23 In the field of aeroelasticity, for any flight vehicle, the states of motion are decided by the inertial force, damping force, elastic force and aerodynamic force, 24 as shown in equation (3)…”

Section: Fluid–structure Interactionmentioning

confidence: 99%

Optimization of the design of ducted-fan hovering micro air vehicles using finite element simulation and orthogonal design

Yang

Wang

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part B:

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The structural design and flight stability characteristics of micro air vehicles have received much attention due to its low Reynolds number. Compared with fixed-wing aircraft, hovering ducted-fan micro air vehicles with vertical takeoff and landing and hovering capabilities have promising prospect. In this article, a flexible membrane and inflatable structure has been used as the aerodynamic shape of an aircraft model. Its advantages have been analyzed and verified by fluidstructure interaction based on finite element method. The flight stability of hovering micro air vehicles has also been investigated based on the theory of motion of structure. In order to improve the flight stability of the designed hovering micro air vehicle model, the effects of geometrical parameters and materials have been analyzed through an orthogonal experimental design. Based on the optimized results, the aircraft prototype has been manufactured for experimental test. The elastic deformation produced on its flexible membrane structure is obtained by stroboscopic stereo imaging method and a purpose-built experimental environment. The numerical simulation results indicated that the thickness of membrane and material of vertical duct have significant effects on the micro air vehicle flight stability and disturbance resistance ability. The results have confirmed that the flexible aerodynamic mechanisms produced by the aeroelastic deformation of spherical membrane can enhance the micro air vehicle stability.

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Fluid/structure interaction in numerical aeroelastic simulation

Cited by 19 publications

References 22 publications

Application of Spectral Method for Vibration-Induced High-Cycle Fatigue Evaluation of an HP Turbine Blade

Application of Spectral Method for Vibration-Induced High-Cycle Fatigue Evaluation of an HP Turbine Blade

Coupled behavior of shape memory alloy-based morphing spacecraft radiators: experimental assessment and analysis

Optimization of the design of ducted-fan hovering micro air vehicles using finite element simulation and orthogonal design

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