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Flight Spectra Development for Fighter Aircraft / NH. Sandlin, RR. Lauridia, DJ. White

Conference Author:
Service Fatigue Loads Monitoring, Simulation, and Analysis (1977 : Atlanta, Ga.)
Physical Description:
1 online resource (14 pages) : illustrations, figures, tables
Additional Creators:
Lauridia, RR., Sandlin, NH., White, DJ., American Society for Testing and Materials, and ASTM International
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Summary:
A method is presented for deriving realistic flight-by-flight stress spectra which are valid for any point in the structure of fighter or attack type aircraft. This method uses regression equations to define the relationships among stresses and flight parameters. The statistical distributions of aircraft motion parameters are derived and defined in multi-parameter response tables. These tables are combined with assigned mission profile data to establish all of the required flight parameters which are used in the regression equations to develop stress spectra. These spectra then are sequenced into a flight-by-flight order which can be used as input to a damage determination model or as a load program for laboratory testing.
Dates of Publication and/or Sequential Designation:
Volume 1979, Issue 671 (January 1979)
Subject(s):
Other Subject(s):
ISBN:
9780803147416 (e-ISBN)
9780803107212
0803107218
Digital File Characteristics:
text file PDF
Bibliography Note:
Includes bibliographical references 6.
Other Forms:
Also available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
Full text article also available for purchase.
Also available in PDF edition.
Reproduction Note:
Electronic reproduction. W. Conshohocken, Pa. : ASTM International, 1979. Mode of access: World Wide Web. System requirements: Web browser. Access may be restricted to users at subscribing institutions.
Technical Details:
Mode of access: World Wide Web.
Source of Acquisition:
ASTM International PDF Purchase price USD25.
View MARC record | catkey: 27986162