Development and validation of preliminary analytical models for aircraft interior noise prediction

Pope, L. D.; Rennison, D. C.; Willis, C. M.; Mayes, W. H.

doi:10.1016/0022-460x(82)90407-2

Cited by 30 publications

(2 citation statements)

References 6 publications

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“…Gathering terms, this becomes (3) where ATL and AABS are changes in IL due to changes in TL and absorption, respectively. Thus, the total insertion loss is a sum of the contributions due to the increases in absorption and transmission loss.…”

Section: Prediction Methodsmentioning

confidence: 99%

Laboratory study of cabin acoustic treatments installed in an aircraft fuselage

Heitman

Mixson

1986

Journal of Aircraft

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The insertion loss of side-wall add-on acoustic treatments was measured using a light aircraft fuselage. The treatments included: no treatment (i.e., baseline fuselage), a production-type double-wall interior, and various amounts of high-density fiberglass added to the baseline fuselage. The source used to simulate propeller noise was a pneumatic-driver with attached exponential horn, supplied with a broadband signal. Data were acquired at the approximate head location for each of the six possible passenger positions. Insertion loss results for the different configurations were analyzed in space-averaged narrowband levels, one-third-octave band levels, and overall levels, and at specific frequencies representing propeller tone spectra. The propeller tone data include not only the space-averaged insertion loss but also the variation of insertion loss of these particular frequencies across the six microphone positions.

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Section: Prediction Methodsmentioning

confidence: 99%

Laboratory study of cabin acoustic treatments installed in an aircraft fuselage

Heitman

Mixson

1986

Journal of Aircraft

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“…Koval [3−4] considered the aircraft fuselage as an infinite cylindrical shell and investigated several areas relevant to the interior noise problem. Pope et al [5] developed a model, by which interior levels in realistic fuselage configurations could be predicted. Blaise et al [6] extended Koval's studies to the case of a plane acoustic wave with two independent angles of incidence in order to calculate the diffuse field transmission coefficient.…”

Section: Introductionmentioning

confidence: 99%

Analytical model of sound transmission through laminated composite cylindrical shells considering transverse shear deformation

Daneshjou

Nouri

Talebitooti

2008

Appl. Math. Mech.-Engl. Ed.

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Composite structures are often used in the aerospace industry due to the advantages offered by a high strength to weight ratio. Sound transmission through an infinite laminated composite cylindrical shell is studied in the context of the transmission of airborne sound into the aircraft interior. The shell is immersed in an external fluid medium and contains internal fluid. Airflow in the external fluid medium moves with a constant velocity. An exact solution is obtained by simultaneously solving the first-order shear deformation theory (FSDT) of a laminated composite shell and the acoustic wave equations. Transmission losses (TL) obtained from numerical solutions are compared with those of other authors. The effects of structural properties and flight conditions on TL are studied for a range of values, especially, the Mach number, stack sequences, and the angle of warp. Additionally, comparisons of the transmission losses are made between the classical thin shell theory (CST) and FSDT for laminated composite and isotropic cylindrical shells.

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