Development Of On-line Satellite Condition Monitoring Module

As the function and structure of satellite, which is the representative ofspacecraft, has becoming increasingly complex, the condition monitoring dataanalysis based diagnosis and health management technology becomes the keytechnique to keep the reliability of satellite system and the stability of the operation.However, data monitoring system of traditional satellite cannot achieve real-timemonitoring and transmission. To solve these problem, this paper researchs on-linesatellite condition monitoring module (OSCMM), which could achieve on-linemonitoring of condition data and provide on-line data processing platform.Base on the analysis of requirements of data interface and processing capacity,this paper takes the power consumption, size, weight and reliability of designconstraints of satellite system into full consideration and proposed the structure of aSOPC based embedded on-line condition monitoring module. It could obtain thesatellite condition monitoring data by relying on standardized bus and networkinterface technology of satellite integrated electronic system, promote dataprocessing capacity by using high performance processor, and provide efficient dataexchange ability though on-chip bus system. The design meets the requirements ofon-line condition monitoring information acquisition and processing, and provideskey technical support for realization of high performance, low power consumption,small size, and embedded machine learning and other complex algorithm.To verify the feasibility of the design, we instantiate the design and develop auniversal and high-performance OSCMM. The module is a3U CPCI board withunobtrusiveness design, and could obtain and transmit satellite condition datathrough SpaceWire or CPCI bus interface. The core processor is a low powerconsumption Zynq-7000AP SoC with heterogeneous processing capacity, its PLpart could increase computing capacity effectively by using parallel computing.Meanwhile, in the SOPC system, we encapsulated the SpaceWire node logic andCPCI bus interface logic into IP cores, which can be connected to AXI4bus. Toenhance the efficiency of data exchange between the data interface and dataprocessing module, we customize a FIFO to AXI4-Stream interface IP core to makeDMA mode available.The experiment results show that the OSCMM could transmit data through SpaceWire at the baud rate of200Mbps, the implementation of floating-pointmatrix multiplication in PL performs better than that in PS, which is up to1333MFLOPS, and in PL, the DMA data transfer speeds through AXI_HP andAXI_ACP ports are all higher than300MB/s. All measured parameters meet thetechnical requirements and embodied rationality of analysis and design. This thesiscould provide important reference to other research and development of unmannedaerospace vehicle fault diagnosis and health management technology.