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Lumped mass modelling for the dynamic analysis of aircraft structuresAircraft structures may be modelled by lumping the masses at particular strategic points and the flexibility or stiffness of the structure is obtained with reference to these points. Equivalent moments of inertia for the section at these positions are determined. The lumped masses are calculated based on the assumption that each point will represent the mass spread on one half of the space on each side. Then these parameters are used in the differential equation of motion and the eigen characteristics are determined. A comparison is made with results obtained by other established methods. The lumped mass approach in the dynamic analysis of complicated structures provides an easier means of predicting the dynamic characteristics of these structures. It involves less computer time and avoids computational errors that are inherent in the numerical solution of complicated systems.
Document ID
19930010271
Acquisition Source
Legacy CDMS
Document Type
Preprint (Draft being sent to journal)
Authors
Abu-Saba, Elias G.
(North Carolina Agricultural and Technical State Univ. Greensboro., United States)
Shen, Ji Yao
(North Carolina Agricultural and Technical State Univ. Greensboro., United States)
Mcginley, William M.
(North Carolina Agricultural and Technical State Univ. Greensboro., United States)
Montgomery, Raymond C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
December 12, 1992
Publication Information
Publication: North Carolina Agricultural and Technical State Univ., The Center for Aerospace Research: A NASA Center of Excellence at North Carolina Agricultural and Technical State University
Subject Category
Aircraft Design, Testing And Performance
Accession Number
93N19460
Distribution Limits
Public
Copyright
Public Use Permitted.
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