Accession Number : AD0416784

Title :   INVESTIGATION OF A METHOD FOR THE PREDICTION OFivvibratory response and stress in typical flight VEHICLE STRUCTURE,

Corporate Author : NORTHROP AIRCRAFT INC HAWTHORNE CALIF

Personal Author(s) : White,R.W. ; Eldred,K.E. ; Roberts,W.H.

Report Date : AUG 1963

Pagination or Media Count : 309

Abstract : The prediction of the vibratory response of a complex structure such as an aircraft fuselage or missile to a random external forcing function was the primary task of this project. Previous attacks on the problem have shown it is not poslbble to estimate vibratory response with useable accuracies. Local and remote acceptance, transmission through structure and to substruc ture, which are all three dimensional phenomena, and randomness are a few of the complexities in volved. The timeliness and importance off the study is due to its concern with structural in tegrity and reliability. The various needs for better handling of new phenomena in structural dynamics are given. Previous studies have indi cated that priority should go to experimental studies, in particular the dynamically similar structural model. The concept is presented along with a demonstration which includes design, con struction, and test of such a model. The ex perimental tool under study will provide a re liability-by-design approach which shortens the design period by providing design inputs early in the development of a new system. The models will be especially useful in space booster projects where different payloads are substituted. Sub studies in support of modeling were conducted. Improved model laws and construction techniques were developed. (Author)

Descriptors :   (*AIRFRAMES, VIBRATION), STRUC, STRESSES, TTEST METHODS, TEST FACILITIES, MODELS (SIMULATION), DESIGN, CONSTRUCTION, MODEL TESTS, SONIC FATIGUE, FAILURE (MECHANICS), SCALE, RELIABILITY.

Distribution Statement : APPROVED FOR PUBLIC RELEASE