In this paper the authors applied the wellknown RAYLEIGH-RITZ'S procedure to the analysis of natural vibration characteristics of plate beam combination structures. General analytical equations were formulated for the structures which consisted of built-up wings and a fuselage. The vibration tests were done on the cantilevered wing, freely suspended built-up delta wing and the built-up delta wings with the fuselage which structurally simulated free-flight model FFM-102) designed to investigate the dynamic characteristics in supersonic flight. The results of the tests were compared with the results obtained from analysis formulated. It was found that both results were in good agreements. It may be concluded that this analytical method is one of the usefull methods for predicting the natural vibration caracteristics of such structures.
The dynamical similarity rules for rigid and articulated rotor blades with a pitch angle are derived. The blade dynamics is described as a linear and elastically coupled vibration system which contains three typical similarity parameters, whose eigen values and eigen functions are numerically determined by the power method. It is found that the effects of the similarity parameters on the vibration characteristics are more dominant for a rigid blade than for an articulated one. It is also shown that dynamical simulation techniques for a rotor blade become easier if composite materials which have high modulus to density ratio, E/ρ, could be utilised.