Oleg A. Kuznetsov
DOI Number: N/A
Conference number: IFASD-2015-036
Structural damping is important in dynamic loading of airplane. In order to show it, this paper provides a brief description of the developed technique. It is based on engineering schematization of airplane structure, modeled by the system of crossed non-uniform beams, acting in bending and torsion. These beams carry the distributed masses and the concentrated ones and the inertia moments. Thus, displacements of airplane are arranged in a number of the products of natural mode shapes by the generalized coordinates. The aerodynamic forces are defined based on the theory of trailing vortex sheet by S.M. Belotserkovsky method. Structural damping is introduced as an additive component into a diagonal of aerodynamic damping matrix. As an example, the regional aircraft weighing about 40 tons and with two engines on the wing is considered. Special attention is given to vertical and lateral accelerations acting at the engine center of gravity. The action of the continuous turbulence is considered. The loading at run on aerodrome cyclic irregularities is explored also. This is done by varying the values of structural damping, including those obtained in the ground vibration tests. The loads maxima are determined.