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Author: Cecil W. Schneider Publisher: ISBN: Category : Languages : en Pages : 218
Book Description
An analytical and experimental program was conducted to develop acoustic fatigue design criteria for aircraft structures subjected to intense noise in a high temperature environment. Equations for the dynamic response of a buckled panel were formulated for simply supported boundary conditions using large deflection plate theory. Random amplitude acoustic fatigue testing of representative aircraft structure was accomplished at temperatures up to 600 F to provide data for correlation with the analytical results. Empirical design criteria are presented in the form of design equations and nomographs for predicting the combined thermal and dynamic response of aircraft structures.
Author: Cecil W. Schneider Publisher: ISBN: Category : Languages : en Pages : 218
Book Description
An analytical and experimental program was conducted to develop acoustic fatigue design criteria for aircraft structures subjected to intense noise in a high temperature environment. Equations for the dynamic response of a buckled panel were formulated for simply supported boundary conditions using large deflection plate theory. Random amplitude acoustic fatigue testing of representative aircraft structure was accomplished at temperatures up to 600 F to provide data for correlation with the analytical results. Empirical design criteria are presented in the form of design equations and nomographs for predicting the combined thermal and dynamic response of aircraft structures.
Author: Cecil W. Schneider Publisher: ISBN: Category : Languages : en Pages : 77
Book Description
An analytical and experimental program was conducted to develop acoustic fatigue design criteria for aircraft structures subjected to intense noise in a high temperature environment. Equations for the dynamic response of a buckled panel were formulated for simply supported boundary conditions using large deflection plate theory. Random amplitude acoustic fatigue testing of representative aircraft structure was accomplished at temperatures up to 600 deg F to provide data for correlation with the analytical results. Empirical design criteria were developed in the form of equations and nomographs for predicting the thermal and dynamic response of aircraft structures subjected to combined environments. The empirical design criteria are presented in handbook format for design use; examples and computer programs are also presented.
Author: Publisher: ISBN: Category : Languages : en Pages : 163
Book Description
The results of an analytic and experimental investigation to identify and determine the influence of effects of structural heating on the dynamic response characteristics of randomly excited aerospace structures and on the combined environment-acoustic fatigue properties of structural components are presented. Thermal and thermal-acoustic tests were conducted on 2024-T81, Ti-6Al-4V and Rene' 41 nickel-base alloy panel specimens. Effects of the temperature increase and sound pressure on the stress response and oil canning of the panels were observed. A semiempirical criterion for predicting oil canning of panels in thermal-acoustic environments was developed. Shaker tests were conducted on 2024-T81 aluminum alloy specimens to determine the effect of the different sequences and combinations of heating and shaker excitation on the fatigue life of the specimens when oil canning is a factor. Elevated temperature fatigue tests under steady-state random (shaker) excitation were also conducted with Ti-6Al-4V titanium alloy and Rene' 41 nickel-base alloy specimens.
Author: Douglas Aircraft Company Publisher: ISBN: Category : Materials Languages : en Pages : 178
Book Description
The effects of compressive loads on structural fatigue at elevated temperatures are investigated using plain, notched, and welded Titanium 8Al-1Mo-1V, and PH 15-7Mo stainless steel coupon specimens. Specimens are subjected to Mach 3 spectrum test environment, including compressive loads. Fatigue life predictions are compared with spectrum teset results. The influence of prior stress-strain history on subsequent life is considered. Prediction methods are extended to include the compression range, and results notched specimens is determined analytically and experimentally. A variety of individual variable fatigue tests are performed at temperatures up to 900F.
Author: J. Y. Mann Publisher: Elsevier ISBN: 1483146456 Category : Business & Economics Languages : en Pages : 572
Book Description
Aircraft Fatigue: Design, Operational and Economic Aspects contains the proceedings of the ""Symposium on Aircraft Fatigue—Design, Operational and Economic Aspects,"" held in Melbourne, Australia, on May 22-24, 1967. The papers explore the design and operational aspects of the fatigue problem in general aviation and transport aircraft, as well as the economic aspects of the fatigue problem as it affects both operators and manufacturers. This book is comprised of 21 chapters and begins with a description of an approach to structural reliability analysis based on order statistics and the expected time to first failure in a fleet of specified magnitude, along with its application to structures subject to progressive fatigue damage. The following chapters deal with structural load measurement and analysis; design and certification programs for a wide range of aircraft types including the Anglo-French and American civil supersonic transports; acoustic fatigue; and the design of joints. The detection of fatigue cracks in service and the effects of fatigue on the cost of design and operation of aircraft are also discussed. This monograph will be a useful resource for aircraft and aeronautical engineers as well as officials of civil aviation.
Author: Elfyn John Richards Publisher: John Wiley & Sons ISBN: Category : Airplanes Languages : en Pages : 532
Book Description
Beskriver detaljeret flystøjs påvirkning af omgivelserne. Nutidens kraftige fly- og raketmotorer producerer voldsomme vibrationer (støj), som kan forårsage træthedsbrud i den omgivende struktur med mindre, der i konstruktionsfasen er taget højde for problemet.
Author: Cecil W. Schneider
Author: Cecil W. Schneider
Author: Cecil W. Schneider
Author: United States. Naval Air Systems Command
Author: 
Author: 
Author: Douglas Aircraft Company
Author: Douglas Aircraft Company
Author: J. Y. Mann
Author: Elfyn John Richards
Author: John E. Duberg