Stress measurement system and method for medium-sized unmanned aerial vehicle wing spar
By combining a distributed fiber optic grating sensing module and a temperature compensation module with a temperature compensation dynamic error compensation algorithm and a dedicated stress calculation model, the problems of large errors and low accuracy in stress measurement of medium-sized UAV wing beams are solved, realizing full-domain, high-precision stress measurement and structural safety assessment.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- XIAN AERONAUTICAL POLYTECHNIC INST
- Filing Date
- 2026-06-11
- Publication Date
- 2026-07-17
AI Technical Summary
Existing methods for measuring stress on the wing spars of medium-sized UAVs suffer from large errors and low accuracy, failing to meet the requirements for high-precision measurement. Furthermore, they fail to effectively consider the anisotropy, temperature coupling effect, and dynamic load fluctuations of composite materials, resulting in significant deviations between the stress calculation results and the actual stress conditions.
The system employs a distributed fiber optic grating sensing module and a temperature compensation module to collect strain values, ambient temperature values, and vibration angular velocity values in real time. Through a temperature compensation dynamic error compensation algorithm and a dedicated stress calculation model, the influence of factors such as temperature and vibration is eliminated, enabling full-domain, high-precision stress measurement.
It achieves full-area, high-precision stress measurement of medium-sized UAV wing spars, reduces measurement errors, provides reliable structural safety assessment data, ensures the stability and accuracy of measurement signals, and is adaptable to medium-sized UAV wing spars of different specifications.
Smart Images
Figure CN122409019A_ABST