Strain sensor, structure monitoring system and manufacturing method

Abstract

The invention relates to a strain sensor, a structure monitoring system and a manufacturing method. The method comprises: directly printing nano metal slurry on a surface of a structure based on a 3Dprinting technique; and solidifying to form a conductive trace for monitoring structural strain. The line has a width as low as tens of microns, a thickness as low as several microns and a small space, can be printed on composite bonding areas with minimal impact on the quality of the bond. The strain sensor, the structure monitoring system and the manufacturing method can be applied to health monitoring of large and complex composite structures. The conductive trace of the invention can realize the sensing of the structural strain and information transmission function through reasonable design, thereby realizing the safety monitoring and evaluation for the structure in total life cycle, and providing the necessary guarantee for the reuse of future advanced aircraft.

Description

technical field [0001] The invention relates to a strain sensor, a structure detection system and a manufacturing method, and belongs to the technical field of composite material structure health monitoring for aerospace vehicles. Background technique [0002] The new generation of advanced aerospace vehicles has the characteristics of long-term on-orbit and multiple uses, which poses challenges to the design, testing, maintenance and status monitoring of traditional structural systems. In order to evaluate the reliability of the aircraft structural system throughout its life cycle, it is necessary to carry out real-time health monitoring of important parts of the structural system. [0003] In order to achieve the goal of lightweight, advanced aerospace vehicles are increasingly using advanced carbon fiber reinforced resin matrix composites to manufacture important components such as cabin skin panels, grille shells, and rudder surfaces. However, the damage form of the com...

AI Technical Summary

Problems solved by technology

However, in the application of composite material structure health monitoring, for composite material parts that require secondary bonding, it is necessary to manually bond the optical fiber to the inner surface of the composite material structure, and then enter the autoclave for secondary curing or secondary bonding , it is prone to the problem of fiber breakage and failure

This is due to the fact that the deformation and expansion rate of the optical fiber is smaller than that of the composite material, so this method is not suitable for composite material structures that need to be cured after the monitoring network is laid.

In the new generation of aerospace vehicle structural systems, the application of composite materials is becoming more and more extensive, and some even reach more than 80% of the amount, and the overall curing, co-bonding and secondary bonding processes are usually used, which are complicated and expensive.

Therefore, it is urgent to develop a new monitoring method that can adapt to the structure of complex composite components to solve the problem of real-time health monitoring of advanced aerospace vehicle composite structures.

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