1977 年 25 巻 277 号 p. 80-94
In this paper the authors applied an analytical method, which was used in the previous paper, Jour. Japan Soc, Aero. Space Sci., Vol. 15, No. 162, by means of the well-known Rayleigh-Ritz's procedure, to the analysis of the natural vibration characteristics of the aircraft structural models.
General analytical equations were formulated for these. Numerical examples were considered for models consisting of combination beam and cantilevered built-up wings, applying the formula to these special cases and a model consisting of a cylindrical fuselage and built-up wings with an aspect ratio of about 7.
At the same time, vibration test of these models were carried out. Comparisons of both results showed that there were fairly good correlations between them, though there are some troubles, which were examined numerically, in the calculation of eigenvalues.
It is concluded that this analytical method cannot be overlooked, as it is one of the most suitable ways of predicting vibration characteristics of these structures in the earlier design phase, although the powerful finite element method is widely applied to these complicated or real airplane structures.