| 摘要 |
A method for the determination of retained strength of an aircraft structure in flight at occurrence of damages, with fighting ones included, wherein one measures simultaneously overloads in the aircraft mass center, at the end and middle sections of the wing, by value of that conclusion is made on load and defectiveness of structure. One measures frequency of natural/autoresonance vibrations of the wing with summing values of overloads measured in the aircraft mass center, at the ends and in the middle section of the wing, with determination of real frequency of natural/autoresonance vibrations of the wing by the absolute value of frequency of natural/autoresonance vibrations of the wing and total value of overload. Then one determines the position of that real frequency of natural/autoresonance vibrations within frequency range of natural/autoresonance vibrations and destructive loads corresponding to those determined preliminarily on earth for numerous damaged states of a similar wing. The level of retained strength of the structure and as result its technical condition is estimated by the value of real frequency of natural/autoresonance vibrations with respect to limiting values of frequencies of natural/autoresonance vibrations of the range, of maximum and minimum frequency, respectively, where minimum frequency of natural/autoresonance vibrations of the wing corresponds to minimum permissible level of its retained strength. |
