Method for actually measuring wing torque loads of high-manoeuvrability aircraft

Abstract

The invention belongs to the field of aircraft flight load actual measurement and relates to a method for actually measuring wing torque loads of a high-manoeuvrability aircraft. The method comprises the following steps: 1, determining a structure or a part sensitive to influences of wing aerodynamic loads on wing torque loads by virtue of wing finite element computation and analysis; 2, realizing a torque load test system for each section of wings by virtue of adopting a sensitive torque bridge piece distribution scheme and a torque bridge combination technology; 3, performing a ground calibration test on the torque loads according to the structure or part sensitive to the influences of the aerodynamic loads on the wing torque loads, thereby obtaining conversion relation between external loads and bridge strain gauge signals by virtue of the ground calibration test; 4, performing a flight load actual measurement flight test, thereby obtaining the torque loads of each section of the wings according to the bridge strain gauge signals during flight. The method has the advantages that by virtue of aiming at the implementation difficulty in aircraft wing torque load actual measurement, the implementation problem of a torque load flight actual measurement test is solved, and the accuracy and high precision of the wing torque load test are ensured.

Description

Technical field [0001] The invention belongs to the field of calculation and analysis of the fatigue life of aircraft structures, and relates to an actual measurement method of the torque load of the wing of a high-mobility aircraft. Background technique [0002] The loads used in the design of the aircraft are mainly obtained through wind tunnel blowing experiments, theoretical calculations and elastic corrections. The load obtained by the load test is the actual load of the aircraft flying. There must be a certain difference between the two types of loads. Therefore, aircraft designers hope to obtain the flight loads through actual measurements, verify the consistency of the design loads with the real loads, and further modify the calculation methods of the design loads. Testing the bending moment, torque and shear force on certain sections of the wing is the most widely used method. The tested bending moment and torque of the wing profile are obtained by the test equipment a...

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Problems solved by technology

[0003] The purpose of the present invention is to solve the above problems, to provide a method for measuring the wing torque load of high maneuvering aircraft, to solve the problem that the torque load cannot be detected or to improve the accuracy of test results during the actual measurement of the wing torque load of high maneuvering aircraft

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