An Evaluation Method of Wind Tunnel Test Balance Based on Strain Signal Energy

Abstract

A wind tunnel test balance assessment method based on strain signal energy mainly includes the steps that a model three-dimensional strain gauge, a framework three-dimensional strain gauge and a balance three-dimensional strain gauge are installed on the inner wall of the top end of an aircraft model, a model framework and a balance respectively; Fourier transformation is carried out on strain signals measured out by the three strain gauges in different directions, then a frequency spectrum signal is obtained, energy normalization characteristic values of six frequency bands within 0-300 Hz are calculated out, the difference value between the energy normalization characteristic values of the strain signals in the same direction of the model and the framework is calculated out, and the difference value between the energy normalization characteristic values of the strain signals in the same direction of the model and the balance is calculated out; when the two difference values between the energy normalization characteristic values in the different directions are within the specialized range, an assessment result determines that test data of the balance are credible, and when the two difference values are not within the specialized range, the assessment result determines that the test data of the balance are not credible. Consequently, model mechanical data measured out through the balance are accurate and reliable in a wind tunnel test, and more accurate and reliable test data are provided for aerospace aircrafts.

Description

Technical field [0001] The invention relates to a calibration and evaluation method of a wind tunnel test balance for aerospace vehicles, in particular to an evaluation method of a wind tunnel test balance based on strain signal energy. Background technique [0002] During the development of aerospace vehicles, in order to understand the performance of the aircraft and reduce the risk and cost of the development of the aircraft, wind tunnel model tests are usually carried out. The measurement of the aerodynamic force and moment received by the aircraft test model under various test conditions is the most basic test item in the wind tunnel test. The test principle is to fix a model support at the bottom of the wind tunnel. The upper end of the model support penetrates into the test model and is screwed to the fixed end of the balance, and the measuring end of the balance is screwed to the model frame in the test model; the model frame The test model is connected by bolts. During...

AI Technical Summary

Problems solved by technology

This calibration method has a long cycle and many steps, and can only calibrate the static characteristics of the balance, and cannot evaluate the dynamic characteristics of the balance under actual working conditions, which leads to the accuracy of the mechanical data of the wind tunnel test under the actual working conditions and the Reliability is difficult to determine, it cannot accurately and reliably evaluate the performance of aerospace vehicles, and cannot provide accurate and reliable test data for aerospace vehicles

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