Real-time impact monitoring instrument and method of large-scale aviation structure

Abstract

The invention discloses a real-time impact monitoring instrument and method of a large-scale aviation structure. The monitoring instrument disclosed by the invention comprises a system power supply module, a signal interface module, a charge amplifier module, an A / D (Analog to Digital) converter module, a programmable logic device module, a control and computing center, a high-capacity onboard high-speed memory module, an external interaction interface and n paths of piezoelectric sensors. The method disclosed by the invention comprises the following steps: the configuration is initialized; strain signals are collected; a charge amplification circuit converts the input charge quantity into the voltage quantity, and the voltage signals are input into a programmable logic device after beingconverted by the A / D converter; the input voltage quantity is firstly compared with the reference voltage digital quantity; when the high level occurs, the channel for triggering the data and the ambient three channels with the maximum signal energy are taken as the effective channel for data storage, and the data of the other channels are abandoned; the region in which the current impact accident occurs and the accurate position in which the impact occurs are judged; and the stored data are transmitted out through the external interface.

Description

technical field [0001] The invention relates to a real-time impact monitor and method for a large-scale aeronautical structure, in particular to an impact signal acquisition occasion for determining the real-time impact area and the precise impact position of a large-scale aeronautical structure, calculating the magnitude of the impact load and the calculation of the impact load history, and can automatically extract the impact The multi-channel effective piezoelectric sensor data when it arrives can work in the master control and slave control modes, and the monitoring data and calculation results are submitted to the external control center through the external bus. Background technique [0002] With a series of advantages such as high specific strength, high specific stiffness, good fatigue resistance and designable material properties, composite materials have been increasingly widely used in aviation, aerospace, automotive and other engineering fields, especially in mili...

AI Technical Summary

Problems solved by technology

[0004] However, for the impact monitoring engineering experiment of large-scale aeronautical structures, taking 24 piezoelectric elements to monitor the impact signal as an example, the monitoring signal is collected according to the traditional high-speed data acquisition test method. The system hardware uses a commercial 4-channel high-speed analog data acquisition card and 4 channel charge amplification conditioner, then to complete the experiment of this project requires at least 6 data acquisition cards and 6 charge conditioners, plus the processor and chassis with unified control core required to integrate this number

A large number of modules with independent application functions and low integration directly lead to an increase in the complexity of the test environment and the difficulty of debugging the test system. At the same time, the cost of hardware and software also brings great difficulties to the development of experiments.

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