A runway structure modal parameter extraction method based on strain sensing

By using a strain-sensing-based method, combined with dynamic strain gauges and the Hilbert-Huang transform algorithm, the influence of aircraft loads is eliminated, and the precise extraction of runway structure modal parameters is achieved. This solves the problems of low accuracy and insufficient real-time performance in traditional methods, enabling real-time monitoring and early warning of runway structure status.

CN117272732BActive Publication Date: 2026-07-24TONGJI UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
TONGJI UNIV
Filing Date
2023-09-21
Publication Date
2026-07-24

AI Technical Summary

Technical Problem

In existing technologies, the methods for calculating runway structural modal parameters suffer from low accuracy and the inability to reflect changes in structural state in real time. In particular, under aircraft loads, traditional methods cannot accurately reflect the dynamic characteristics and structural health of the runway.

Method used

By employing a strain-sensing-based approach, data is collected through dynamic strain gauges. Combined with finite element theory and Hilbert-Huang transform algorithm, the influence of aircraft self-weight load is eliminated, and the modal parameters of the runway structure are accurately extracted.

Benefits of technology

It achieves accurate calculation of runway strain modal parameters, can reflect structural state changes in real time and sensitively, has strong adaptability, is suitable for the analysis of a large amount of online strain data, and improves the calculation accuracy of modal parameters and real-time early warning capability.

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Abstract

The application discloses a runway structure modal parameter extraction method based on strain sensing, and comprises the following steps: strain data acquisition and storage; determining the real-time position of an airplane landing gear wheel shaft through a strain gauge; determining the airplane vertical equivalent load at the strain gauge measuring point; constructing a node self-weight load time history curve U f ( K ); strain sensing data preprocessing; obtaining a strain time history curve Yp(K) containing effective peak value information; eliminating the influence of the load on modal parameter identification; according to the determined subspace projection theory, using the obtained strain time history curve containing effective peak value information and the determined input to construct a node airplane equivalent load to construct an orthogonal projection matrix P(K) ; then multiplying the strain time history curve containing effective peak value information with the projection matrix, projecting the dynamic strain to a subspace irrelevant to the airplane self-weight load, and eliminating the influence of the airplane self-weight load on the dynamic strain; and runway structure strain modal parameter calculation.
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