Research On Fault Injection And Fault Monitoring Technology Of G1000 System

With the advancement of aviation electronic system architecture and aviation bus technology,the internal structure complexity and comprehensive modularity of general aircraft avionics systems are constantly increasing,which presents a great challenge for the localization of avionics systems in China.In this context,by injecting faults into real components and conducting fault monitoring testing,not only can the labor cost of fault maintenance be reduced and the maintenance cycle shortened,but also it can provide assistance for the localization of avionics systems.The fault injection and fault monitoring techniques,the structural framework and internal component interconnection and interface information of the G1000 system,ARINC429,RS232,and RS485 bus standards,are thoroughly investigated in this article,and common fault types of the G1000 system are summarized and concluded.Then,hardware fault injection method is selected,and the real components of the G1000 system of a Cessna 172 aircraft are used as the experimental object,with fault monitoring carried out through the data bus.The main research content and contributions of this thesis are as follows:(1)A hardware fault injection system scheme for the G1000 avionics system is proposed.Fault injection is divided into physical and electrical layers.The physical layer uses a switch panel to inject power and plug faults into each component of the G1000 system.Taking the GEA 71 component as an example,an electrical fault injection equipment scheme for the GEA 71 component is proposed,which can inject controllable analog signals and pulse signals into the interface of the GEA 71 component without damaging the component.The equipment is divided into a lower computer and an upper computer.The lower computer uses STM32F103 RC as the main control chip,and the hardware circuit design is described.The upper computer designs the system interface through Qt software development,and interacts with the lower computer through a USB interface.(2)A fault monitoring scheme for data bus is proposed.Based on the working mechanism of the G1000 system,a fault monitoring system is built using the RS-PCI-8MI serial card and ARINC429 card.Through the interface between each component and the GIA63 data transmission,the RS232,RS485,and ARINC429 data buses of the G1000 system are collected and monitored in real-time to observe and record the changes in the internal state of the G1000 system(such as fault flags and system-information pages).(3)In this thesis,after fault injection and fault monitoring tests,the data paths of each component of the G1000 system are successfully verified,while data analysis is performed on the injected GEA 71 electrical layer fault signals and the G1000 system display values to obtain GEA 71 sensor fitting curves and equations,and preliminary analysis of the collected RS485 bus data is completed.