FIELD: aircraft engineering.
SUBSTANCE: first, reference specimens are used the dependence of structural material damping capability on various factors. Then, aircraft airframe natural structure is used at the ground to define the dynamic characteristics including the dependence of oscillation damping parameters on various parameters for the airframe intrinsic flexible modes. Then, calculated is the list of conservative natural flexible modes of aircraft airframe structure in the range of flight cruising speeds. Then, in flight at identical modes symmetric or asymmetric deflection of aircraft control members is used to excite the harmonic or polyharmonic oscillations. At the start of planned operation and at specified period measured data of oscillation transducers arranged at controlled structural elements are used as well as aircraft forces oscillation excitation forces to define the dynamic characteristics of the main harmonic and nonlinear oscillations for conservative modes. Negative change in oscillation damping parameters in aircraft operation indicates the deterioration of the strength performances of structural elements.
EFFECT: higher accuracy of determination of aircraft structural elements.
3 dwg
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