The invention provides a spacecraft structure multi-functional health monitoring system and method, which are used for solving the problems of excessive spacecraft monitoring equipment and no data integration in the prior art. According to the spacecraft structure multi-functional health monitoring method, a data integration processing module is connected with an external power supply and transmits the data to other modules, set acquisition parameters and acquisition start and stop instructions are issued to the other modules, and three monitoring modules acquire data and then send the data tothe data integration processing module; and after the collected data is received, the structure temperature, the strain state, the elastic guided wave and the acoustic emission data are integrated, and the temperature curve, the crack damage, the collision damage and the leakage state are analyzed and displayed. According to the invention, integrated acquisition and data integration and analysisof multiple parameters of the spacecraft structure are realized, health states such as geometric structure, strain and temperature of the spacecraft are monitored more efficiently and conveniently, early warning is carried out on damages such as cracks, collision and leakage, and the safety and reliability of the spacecraft are ensured.
本发明提供了一种航天器结构多功能健康监测系统和方法,用以解决现有技术中对航天器监测设备过多、无数据整合的问题。所述航天器结构多功能健康监测方法,通过数据集成处理模块连接外部电源并传递给其他模块,同时为其他模块下发设置的采集参数、采集开始、停止指令,三大监测模块采集完数据后发送至数据集成处理模块;在接收采集数据后,整合结构温度、应变状态、弹性导波及声发射数据,分析温度曲线、裂纹损伤、碰撞损伤及泄漏状态并进行显示。本发明实现了航天器结构多参数的集成采集、数据整合与分析,更高效更便捷地对航天器的几何结构、应变、温度等健康状态进行监测,对裂纹、碰撞和泄漏等损伤进行预警,确保航天器的安全性和可靠性。
Spacecraft structure multi-functional health monitoring system and method
一种航天器结构多功能健康监测系统和方法
2021-01-22
Patent
Elektronische Ressource
Chinesisch
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