METHOD FOR EXPERIMENTAL DETERMINATION OF BENDING STIFFNESS OF AIRCRAFT ELEMENTS Russian patent published in 2025 - IPC G01M5/00 G01N3/20 

FIELD: aerospace industry.

SUBSTANCE: proposed method of determining bending stiffness of aircraft elements can be used when testing any aircraft elements with high elongation. Method comprises the following sequence of operations. One end of aircraft element is fixed in horizontal position. In one zone of the part of the power set of the aircraft element frame, the area for determining the bending stiffness of the aircraft element is marked along the axis of its stiffness, thereby determining cross-sections A, B and C. Sections A and C are extreme sections of the region for determining bending stiffness of the aircraft element, and section B is the middle section of the region for determining bending stiffness of the aircraft element. Further, the bases of the two halves of the curvature gauge are installed on fixed supports, which rest on the aircraft element in the area of determining bending stiffness of the wing (ABC area). Then, using vacuum clamps, the curvature meter is fixed on the wing and linear displacement transducers are switched on. Thereafter, adjustable supports are used to achieve parallelism of installation of the stand – support of optical sensors and the stand intended for determining the distances between the sensors and this stand, wherein the distance between the stands is fixed according to the readings of the lower and upper sensors. Further, the free end of the aircraft element is loaded with a concentrated force P or a concentrated bending moment M. New distances between the supports are fixed according to the readings of the lower and upper sensors and the angle of rotation of the posts α is calculated between loaded and unloaded concentrated force or concentrated bending moment states of aircraft element. Using turning angle α, average bending stiffness of the aircraft element in the area of its determination (in the area of ABC) is determined.

EFFECT: reduced error of the determined radius of curvature of the area of experimental determination of bending stiffness of the tested aircraft element and, accordingly, reduced error of the determined average bending stiffness of this element in the area of its experimental determination.

1 cl, 2 dwg