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Evaluation of Several Approximate Methods for Calculating the Symmetrical Bending-Moment Response of Flexible Airplanes to Isotropic Atmospheric TurbulenceSeveral approximate procedures for calculating the bending-moment response of flexible airplanes to continuous isotropic turbulence are presented and evaluated. The modal methods (the mode-displacement and force-summation methods) and a matrix method (segmented-wing method) are considered. These approximate procedures are applied to a simplified airplane for which an exact solution to the equation of motion can be obtained. The simplified airplane consists of a uniform beam with a concentrated fuselage mass at the center. Airplane motions are limited to vertical rigid-body translation and symmetrical wing bending deflections. Output power spectra of wing bending moments based on the exact transfer-function solutions are used as a basis for the evaluation of the approximate methods. It is shown that the force-summation and the matrix methods give satisfactory accuracy and that the mode-displacement method gives unsatisfactory accuracy.
Document ID
19980230604
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Bennett, Floyd V. (NASA Langley Research Center Hampton, VA United States)
Yntema, Robert T. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1959
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-MEMO-2-18-59L
L-143
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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