Intrinsically tuned structural panel

Details Intrinsically tuned structural panel Intrinsically tuned structural panel

1974-12-19

1976-08-24

Steiner, Arthur J.

Aeronautics and astronautics

Aircraft structure

Fuselage and body construction

29191, 52144, 52629, 181 33A, 181 33G, 244132, B64C 112

Patent

active

039762696

ABSTRACT:
A structural panel of the skin-stiffener type, commonly used in aircraft construction, having significantly reduced vibration response, noise radiation and increased acoustic fatigue life, has a skin supported by uniformly spaced stiffeners which are located such that the fundamental natural frequencies of stiffener segments are equal to the fundamental natural frequency of skin sub-panels between the stiffener segments. The physical and geometric properties of the skin and stringers and the spacing of the stringers in various disclosed embodiments depend upon the trace velocity of the excitation field, loading conditions to which the panel is subjected, and end-conditions of the sub-panels and stiffeners.

REFERENCES:
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patent: 3771748 (1973-11-01), Jones
"The Design of Structures to Resist Jet Noise Fatigue", Clarkson, The Journal of the Royal Aeronautical Society, vol. 66, No. 622, 10/62, pp. 603-616.

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