Structural Uncertainty Effect on Classical Wing Flutter Characteristics

Borello, Fabio; Cestino, Enrico; Frulla, Giacomo

doi:10.1061/(asce)as.1943-5525.0000049

Cited by 34 publications

(19 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There is a satisfactory matching with another 2D approximation of the straight wing model [20], while the discrepancies with an aeroelastic model comprising 3D eects [18] remain below 3% in terms of V f . In this regard, it is remarked here that, although the aspect ratio of the Goland wing is not considered to be high, the model proposed in Sec.…”

Section: A Restrained Wing Model Validationmentioning

confidence: 90%

Study of Flexible Aircraft Body Freedom Flutter with Robustness Tools

Iannelli

Marcos

Lowenberg

2018

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms Features that complicate its study are the presence of multiple modal instabilities, and the dierent inuence that system parameters have on each of them. The robust analysis framework based on Linear Fractional Transformation modeling and structured singular value µ analysis is used in this work to study the BFF problem in a systematic way. The analyses performed showcase the potential of these methods, not only in supplying a characterization of the system in terms of its robustness, but also in gaining further understanding of the BFF problem and reconciling the results with physical features. It is also shown that the robust modeling analysis framework complements the conventional, state of practice, methods while allowing the study of highly coupled systems (of which the exible aircraft is an example) to be addressed in an incremental and methodological manner.

show abstract

Section: A Restrained Wing Model Validationmentioning

confidence: 90%

Study of Flexible Aircraft Body Freedom Flutter with Robustness Tools

Iannelli

Marcos

Lowenberg

2018

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

show abstract

“…Other surrogate modelling techniques have been used in the reliability-based design of composite wings, for example, Manan and Cooper (2009) minimised the probability of aeroelastic instability occurring in composite plate wings at a specified air-speed using a Polynomial Chaos Expansion surrogate model. Additionally, polynomial response surfaces were used by Borello et al (2010) for estimating the reliability with respect to the flutter speed of both metallic and composite wings with uncertain material properties.…”

Section: Introductionmentioning

confidence: 99%

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

Scarth

Cooper

2017

Struct Multidisc Optim

View full text Add to dashboard Cite

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.

show abstract

“…In the aeroelastic computation, inherent modeling uncertainties present in the structural and aerodynamic systems and inaccuracies in the measurements demands uncertainty quantifica tion. As a result, the probabilistic methods have recently received considerable amount of attention [35,36,37,12,38,39]. Some of these methods include simple Monte Carlo Sim ulation (MCS), perturbation method and spectral methods [11,40].…”

Section: Deterministic Aeroelastic Fluttermentioning

confidence: 99%

“…Next, a short overview of the UQ methods and some of their applications in the field of aeroelasticity is provided. Due to large computational costs associated with the probabilistic analysis, some authors prefer to conduct a sensitivity analysis in order to identify the most significant pa rameters influencing the output [36,42,43]. This method is based on a Taylor Series expansion of the response around the baseline parameter value.…”

Section: Uncertainty Quantificationmentioning

confidence: 99%

“…Using MCS Bansal et al found that the chord-wise location of mass center and torsional rigidity had the most influence on the uncertainty of the flutter speed. The effects of structural uncertainty were also studied by Borello et al [36], whereby different reliability methods are compared with respect to the results of MCS. Using a rigid wing model, this work investigated the influence of different amounts of structural parameter uncertainty on the flutter speed to assess the ac curacy of the reliability methods.…”

Section: Probabilistic Flutter Speed Estimationmentioning

confidence: 99%

See 1 more Smart Citation

Parametric uncertainty quantification in coalescene flutter

Matachniouk¹

View full text Add to dashboard Cite

Structural Uncertainty Effect on Classical Wing Flutter Characteristics

Cited by 34 publications

References 22 publications

Study of Flexible Aircraft Body Freedom Flutter with Robustness Tools

Study of Flexible Aircraft Body Freedom Flutter with Robustness Tools

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

Parametric uncertainty quantification in coalescene flutter

Contact Info

Product

Resources

About