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  • Open Daily: 10am - 10pm
    Alley-side Pickup: 10am - 7pm

    3038 Hennepin Ave Minneapolis, MN
    612-822-4611

Open Daily: 10am - 10pm | Alley-side Pickup: 10am - 7pm
3038 Hennepin Ave Minneapolis, MN
612-822-4611
Finite and Boundary Element Modeling of the NASA Langley Aluminum Testbed Cylinder

Finite and Boundary Element Modeling of the NASA Langley Aluminum Testbed Cylinder

Grosveld, Ferdinand W.
Nasa Technical Reports Server (Ntrs)

Paperback

General Political Science

ISBN10: 1287249280
ISBN13: 9781287249283
Publisher: Bibliogov
Published: Jul 29 2013
Pages: 80
Weight: 0.35
Height: 0.17 Width: 7.44 Depth: 9.69
Language: English
The NASA Langley Aluminum Testbed Cylinder (ATC) was designed to serve as a universal structure for evaluating structural acoustic codes, modeling techniques and optimization methods used in the prediction of aircraft interior noise. Finite element models were developed for the components of the ATC based on the geometric, structural and material properties of the physical test structure. Numerically predicted modal frequencies for the longitudinal stringer, ring frame and dome component models, and six assembled ATC arrangements were in good agreement with experimental modal survey data. Finite element modal analyses were performed for 3 psi and 6 psi internal pressurization conditions. Acoustic cylinder modes for the interior of the ATC were calculated with an acoustic finite element model. Frequency transfer functions between a unit force on the structure and the acoustic response inside the ATC cylinder were measured and were compared with predictions based on a boundary element model. Comparisons between predicted and experimental results are presented and discussed.

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