Structural Design for Acoustic Fatigue PDF Download

Author: Douglas Aircraft Company
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: DOUGLAS AIRCRAFT CO INC LONG BEACH CALIF.
Publisher:
ISBN:
Category :
Languages : en
Pages : 119

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Results of either descretely or randomly excited structural acoustic tests are extended through an analytical approach and these results are presented as design nomographs. The source of acoustic excitation was considered to be the propulsion system; the structure of main interest was the lighter structural configuration common to wing trailing edges, empennage, or fuselage afterbody. These structural components are most commonly exposed to acoustic environments and are such that other design criteria are not critical. The design results are presented as a function of the allowable random fatigue life of the material. Use of elevated temperature data for this fatigue life would account for the direct effect on the material of elevated temperature. No attempt was made to account for the over-all effect of elevated temperature; this depends so greatly on the response of the adjoining structure that it is beyond the scope of this study. Additionally, for a majority of the structural components under study the damage occurs at takeoff when temperatures are nominal and combined effects are insignificant. (Author).

Author:
Publisher: ASTM International
ISBN:
Category :
Languages : en
Pages : 224

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Author: Fred F Rudder (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 193

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Analytical results for estimating natural frequencies and stress response for conventional stiffened flat panels, two-sided box structure, wedge structure, and unstiffened cylindrical panels are presented. Acoustic fatigue tests of twelve stiffened flat panel and six box structure designs, two specimens for each design, were used to develop design equations for estimating acoustic fatigue resistance of skin, stringer, and rib structure. Computer programs are presented for estimating frequencies of stiffened flat panels, box structure, and wedge structure. Nomographs are presented for skin design and curved panel stress response. (Author).

Author: Edward M. Lenoe
Publisher: Springer Science & Business Media
ISBN: 1468410334
Category : Technology & Engineering
Languages : en
Pages : 858

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The Fourth Conference on Fibrous Composites in Structural Design was a successor to the First-to-Third Conferences on Fibrous Composites in Flight Vehicle Design sponsored by the Air Force (First and Second Conferences, September 1973 and May 1974) and by NASA (Third Conference, November 1975) which were aimed at focusing national attention on flight vehicle applications of a new class of fiber reinforced materials, the advanced com posites, which afforded weight savings and other advantages which had not been previously available. The Fourth Conference, held at San Diego, California, 14-17 November 1978, was the fi rst of these conferences to be jointly sponsored by the Army, Navy and Ai r Force together with NASA, as well as being the first to give attention to non-aerospace applications of fiber reinforced composites. While the design technology for aerospace applications has reached a state of relative maturity, other areas of application such as mi litary bridging, flywheel energy storage systems, ship and surface vessel components and ground vehicle components are in an early stage of development, and it was an important objective to pinpoint where careful attention to structural design was needed in such applications to achfeve maximum structural performance payoff together with a high level of reliability and attractive economics.

Author: A. G. R. Thomson
Publisher:
ISBN:
Category :
Languages : en
Pages : 46

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The report contains acoustic fatigue test procedures, methods of calculation and results for various structural elements. Section I presents a method to determine the natural frequencies of initially unstressed box structures that are rectangular in section. The second section provides a method of estimating the R.M.S. stress in internal plates of a box structure subjected to random acoustic loading. Section III provides a method of estimating the sound pressure levels within the intake duct of a supersonic fan or compressor due to buzz saw noise.

Author: Ying Xiao
Publisher:
ISBN:
Category :
Languages : en
Pages : 292

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Author: Chunyun Niu
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 632

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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN: 9789283600015
Category : Aerodynamic load
Languages : en
Pages :

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Author: A. G. R. Thomson
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 254

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