Dynamic qualification of the HIRENASD elastic wing model

Korsch, H.; Dafnis, Athanasios; Reimerdes, Hans-Günther

doi:10.1016/j.ast.2008.08.002

Cited by 16 publications

(11 citation statements)

References 4 publications

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“…Thus, it can be concluded that the SL model can represent the aluminum prototype in the prediction of dynamic behaviors. That is to say, the new method presented in this paper is a feasible solution to the design and fabrication of aeroelastic models for wind tunnel tests (Korsch et al , 2009; Kampchen et al , 2003; Jonathan et al , 2008).…”

Section: Resultsmentioning

confidence: 96%

“…The implementation of optimization should be improved to enhance the efficiency and the accuracy: the number of design variables could be reduced through sensitivity analysis, the errors of the locations of centroid might decrease by adjusting the locations of balance‐weights, etc. It should be noticed that the correlation of natural modes between the model and the prototype should be studied except for natural frequencies (Korsch et al , 2009). Thus, the design procedure must be extended to include optimization of natural modes of the model.…”

Section: Resultsmentioning

confidence: 99%

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Design and fabrication of stereolithography‐based aeroelastic wing models

Zhu

Li²,

Zhang³

et al. 2011

Rapid Prototyping Journal

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PurposeThe purpose of this paper is to present a novel method to design and fabricate aeroelastic wing models for wind tunnel tests based on stereolithography (SL). This method can ensure the structural similarity of both external and internal structures between models and prototypes.Design/methodology/approachAn aluminum wing‐box was selected as the prototype, and its natural modes were studied by FEA and scaled down to obtain the desired dynamic behavior data. According to similarity laws, the structurally similar model was designed through a sequential design procedure of dimensional scaling, stiffness optimization and mass optimization. An SL model was then fabricated, and its actual natural modes was tested and compared with the desired data of the prototype.FindingsThe first two natural frequencies of the model presented strong correlation with the desired data of the prototype. Both the external and internal structures of the model matched the prototype closely. The SL‐based method can significantly reduce the total mass and simplify the locating operations of balance‐weights. The cost and time for the fabrication were reduced significantly.Research limitations/implicationsFurther investigation into the material properties of SL resins including stiffness and damping behaviors due to layered process is recommended toward higher prediction accuracy. Wind tunnel tests are needed to study the in situ performance and durability of SL models.Originality/valueAlthough the paper takes a wing‐box as the study object, structurally similar SL models of entire wings can be obtained conveniently, benefiting from the low‐stiffness material properties of SL resins and the fabrication capacity to build complex structures of SL process. This paper enhances the versatility of using SL and other rapid prototyping processes to fabricate models to predict aeroelastic characteristics of aircraft.

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Section: Resultsmentioning

confidence: 96%

Section: Resultsmentioning

confidence: 99%

Design and fabrication of stereolithography‐based aeroelastic wing models

Zhu

Li²,

Zhang³

et al. 2011

Rapid Prototyping Journal

View full text Add to dashboard Cite

show abstract

“…Wind-off modal survey data was acquired for the HIRENASD by hammer impact test and by frequency sweeps of the piezoelectric stack actuators. 11 However, the modeshapes and the data acquired during those tests were not available. The only dataset available for extracting mode shapes was acquired by exciting the HIRENASD wind-tunnel model with a 35 Hz excitation of the piezoelectric stack actuators.…”

Section: A Modal Frequenciesmentioning

confidence: 99%

“…10,11 It was therefore decided to include more detail in the finite element model (FEM) to improve the correlation with experiment by making appropriate structural changes to the original solid element model to correspond better with the actual structure. T This paper documents the changes to the HIRENASD FEM that were made during the development of a standardized FEM to be used to support the AePW, validation of the FEM development and Computational Fluid Dynamics (CFD) results using modes from the original wing-only FEM and the final modified model.…”

Section: Introductionmentioning

confidence: 99%

“…The third test case selected for this initial workshop was the HIgh REynolds Number Aero-Structural Dynamics (HIRENASD). 7,8,9,10,11 The HIRENASD model was chosen as an initial coupled aeroelastic analysis configuration. The wing has a high degree of structural stiffness and broad spacing of the structural modes, which produces weak aeroelastic coupling and makes it a good entry-level basis of evaluation.…”

Section: Introductionmentioning

confidence: 99%

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