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- W2567528088 abstract "The results of static strength tests from different types of aircraft structures and structural parts obtained from several aircraft manufacturers were statistically analyzed. By using test samples with at least 3 replications and reducing sample data to their mean, all results could be unified in a single population of over 300 data points and these points fitted by the third asymptotic distribution of smallest values (Weibull distribution). This distribution is used as a representative distribution of the strength of an aircraft combined with the ratio between the design load and the strength attained in actual tests, derived from the test data. By combining the distribution of strength with representative distributions of gusts in flight through thunderstorm turbulence and of operational loads, respectively, realistic reliability functions for load of gust-sensitive (long-range) and of maneuver-sens itive (short-range) aircraft structures were obtained for various assumed levels of the design load. T is the purpose of this study to estimate the structural reliability of critical parts of airframes on the basis of strength test data of aircraft structures from various sources and of the spectrum of extreme gust and maneuver loads. The third asymptotic distribution function of extreme (smallest) values (Weibull distribution) has been chosen to fit the strength data obtained from tests on aircraft structural parts. Thus, the strength of any one member of the airframe can be expressed in terms of its design load with the aid of this distribution function. A comparison is made between the recently obtained test data and the test results obtained by the Air Force about 20 years ago.1 This comparison throws some light on certain aspects of aircraft structural development during this period. Representative thunderstorm and flight load spectra are adopted to match the distribution function of strength, and the risk of ultimate load failure is computed according to a standard procedure developed for this purpose2 by assuming various values of the design gust or load factor. The associated reliability functions are subsequently evaluated in terms of the number of load application or of flight time of the aircraft. 2. Analysis of Data" @default.
- W2567528088 created "2017-01-06" @default.
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- W2567528088 date "1970-01-01" @default.
- W2567528088 modified "2023-09-26" @default.
- W2567528088 title "Ultimate Strength Analysis of Aircraft Structures" @default.
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