Technology Laboratory Program Of Aircraft Health Monitoring And Verification Model

Health monitoring is currently the topic of significant research. It has been applied to civil structures such as bridges, highways, power plants, tunnels, etc. The application of health monitoring to air transportation systems and vehicles (spacecraft, aircraft, helicopters, etc.), and high-valued manufactured products (satellites, launch systems, etc.) is crucial to increase operational efficiency, reliability, security, reduce maintenance cost, and prevent catastrophes. In those advanced countries such as America, Russia, Europe and Japan, aircraft health monitoring technique was researched with a lot of resources. While in China, there was a little related researches, say nothing of many applications. In order to catch up with overseas, it needs not only sensing technology development, a lot of researchers who devote to methods and theories researches, but also an aircraft health monitoring laboratory for validation of their schemes.This thesis presents an aircraft health monitoring laboratory design scheme. Based on virtual instrument technique, the laboratory is constructed with basic hardware and varied developed signal processing, diagnosis, and health monitoring computer programs. This scheme makes it flexible, economical, and time-saved for various kinds of research. Aircraft Health Monitoring System requires remote, real-time, high accuracy, robust and self-repairing capabilities. As a whole, it consists of three main subsystems: Data Acquisition System (DAS), Data Transportation System (DTS) and Data Processing System (DPS). In the second chapter of this thesis discuss the architecture, instrumentations and related techniques of DAS, the remote, wireless, spread spectrum based DTS, and the Signal Processing System (SPS) and Diagnosis System (DS) of DPS.For validating the feasibility, generality, and validity of the laboratory design scheme, chapter 3 presents a demonstration model, which uses the fuel system of an aeromodelling as the research object. The main distinct points are: the development of virtual press sensor and virtual fuel flowmeter for simulating the fuel system statusdata, the Digital Signal Processing for the SPS, and the diagnosis method-System Status Factor Fault Diagnosis. The results show that the method can distinguish the four typical faults of the fuel system, and the scheme can realize aircraft health monitoring.In the end I summarize the whole thesis and view the related techniques's development in the future of this laboratory.