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为提高微小卫星姿控系统的集成度、实时性、灵活性和可扩展性,本文运用SoPC技术设计了一种基于NiosⅡ双核架构的微小卫星姿态控制器。在一片FPGA内嵌入2个NiosⅡ软核,分别处理外设通信和姿控算法,双核通过共享存储器实现信息交互。该系统还封装了自行设计的外设接口IP核和各类数学运算IP核,分别实现多路并行外设通信和姿控算法的硬件加速。该系统也可以在上述基础上针对不同的应用需求,封装不同的IP核以实现系统的扩展和性能的提升。本文从构架设计、硬件选型、软件编排和任务调度等角度对系统进行了描述,最后以三轴气浮台模拟卫星本体作为控制对象,进行了全物理仿真实验,实验结果的统计表明,该姿态控制器功能齐全,性能稳定,可应用于实际的微小卫星姿控系统。
In order to improve the integration, real-time, flexibility and scalability of micro-satellite attitude control system, this paper designs a micro-satellite attitude controller based on NiosⅡ dual-core architecture using SoPC technology. In a FPGA embedded Nios Ⅱ 2 soft core, respectively, dealing with peripheral communication and attitude control algorithms, dual-core shared memory through the exchange of information. The system also encapsulates its own design of the peripheral interface IP core and various types of mathematical computing IP core, respectively, to achieve multiple parallel peripherals communication and attitude control algorithm hardware acceleration. The system can also be based on the above for different application needs, different IP core package to achieve system expansion and performance improvements. In this paper, the system is described from the perspectives of architecture design, hardware selection, software layout and task scheduling. Finally, the full-body simulation experiment is carried out on the three-axis air-flotation platform simulating satellite ontology. The experimental results show that the Attitude controller full-featured, stable performance, can be applied to the actual micro-satellite attitude control system.