Aircraft interior noise models: Sidewall trim, stiffened structures, and cabin acoustics with floor partition

Pope, L. D.; Wilby, E. G.; Willis, C. M.; Mayes, W. H.

doi:10.1016/0022-460x(83)90544-8

Cited by 19 publications

(5 citation statements)

References 6 publications

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“…From Ref. 7, the unmodified shell response appears to be governed by the (3,4), (5,7), (5,8), and (5,9) structural modes, all of which have resonant frequencies below the driving frequency of 680 Hz. Results by Pope et al 11 indicate that off-resonance response of the shell can be governed by a number of stuctural modes whose resonance frequencies are above and/or below the driving frequency.…”

Section: Driving Frequency Of 680 Hzmentioning

confidence: 97%

Influence of a floor on sound transmission into an aircraft fuselagemodel

Jones

Fuller

1988

Journal of Aircraft

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A simplified cylindrical model of an aircraft fuselage is used to study experimentally the effect of an internal floor on low-frequency sound transmission into aircraft cabins. A geometrically scaled lattice floor support and floor skin are designed based on selected characteristics of a business aircraft. The pressure amplitude at various interior locations is presented along with a modal decomposition of the associated shell response. Results indicate that the main effect of the floor on interior pressure levels is due to a modification of the interior acoustic mode shape and not due to the structural modification of the fuselage model caused by the lattice floor support. Thus, the model provides a simplified procedure for studying the influence of various structural modifications as well as other important effects. Nomenclature a = radius of test cylinder, 0.254 m A n = complex modal amplitude coefficients, Eq. (la) B n = complex modal amplitude coefficients, Eq. (lb) / = frequency (Hz) m = number of axial half waves n = circumferential mode number N p = number of measuring positions p = 1,2,3,...,r ,Q,x = cylindrical coordinates w = radial displacement e n = Neumann factor: e 0 = 1; e n = 2, n > 0

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Section: Driving Frequency Of 680 Hzmentioning

confidence: 97%

Influence of a floor on sound transmission into an aircraft fuselagemodel

Jones

Fuller

1988

Journal of Aircraft

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“…In some cases, e.g. aircraft fuselages, the curvature is low enough to be neglected in a first order approximation [117].…”

Section: Extensionsmentioning

confidence: 99%

Modelling Techniques for Vibro-Acoustic Dynamics of Poroelastic Materials

Deckers

Jonckheere

Vandepitte

et al. 2014

Arch Computat Methods Eng

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“…In turn these indicators, with the diffuse field absorption and the transmission loss, can be used within SEA framework to account for the effect of sound package in full system configurations, such as cars or aircraft (Pope et al 1983, Atalla et al 2004. In turn these indicators, with the diffuse field absorption and the transmission loss, can be used within SEA framework to account for the effect of sound package in full system configurations, such as cars or aircraft (Pope et al 1983, Atalla et al 2004.…”

Section: Other Applicationsmentioning

confidence: 99%

Extensions to the Transfer Matrix Method

Allard

Atalla

2009

Propagation of Sound in Porous Media

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This chapter discusses various extensions and applications of the transfer matrix method (TMM). First, corrections to account for size effects in absorption and transmission loss problems are presented with validation examples. Next, the application of the method to point load excited panels with attached sound packages is discussed. Finite size correction for the transmission problemThe classical transfer matrix method assumes a structure of infinite extent. For transmission loss application, the method correlates well with experiments at mid to high frequencies for a large range of flat panels. Discrepancies are however observed at low frequencies, especially for panels of small size. This section presents a simple geometrical correction to account for this 'geometrical' finite size effect (Ghinet and Atalla, 2002). The rationale behind the approach presented is to replace the radiation efficiency in the receiving domain by the radiation efficiency of an equivalent baffled window. This approach is thus strictly valid for planar structures. Transmitted powerConsider a baffled panel of area S excited by a plane incident wave with heading angles(θ, φ)p i (M) = exp −jk 0 (cos φ sin θx + sin φ sin θy + cos θz) (12.1) Propagation of Sound in PorousMedia: Modelling Sound Absorbing Materials, Second Edition J. F. Allard and N. Atalla

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Aircraft interior noise models: Sidewall trim, stiffened structures, and cabin acoustics with floor partition

Cited by 19 publications

References 6 publications

Influence of a floor on sound transmission into an aircraft fuselagemodel

Influence of a floor on sound transmission into an aircraft fuselagemodel

Modelling Techniques for Vibro-Acoustic Dynamics of Poroelastic Materials

Extensions to the Transfer Matrix Method

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