基于1553B总线三冗余飞行控制系统设计与可靠性研究

TMR Design of FCS Based on 1553B Bus and Reliability Analysis

摘要:

对系统可靠性的探讨一直是航天飞行器设计过程中的首要议题，飞行控制系统作为核心系统，一旦出现故障会导致整个飞行任务的失败。以提升飞行可靠性需求为出发点，提出了一种基于1553B总线的飞行控制计算机三冗余设计方案，给出了冗余飞控系统的架构设计、控制板硬件构成、三模块同步方案和表决算法等设计方法，完成了飞行控制系统的冗余设计策略研究。为适应飞控系统的国产化、小型化、轻质化设计趋势，采用了基于国产SoC芯片的SiP模块以实现工程化。为研究三冗余系统方案可靠性，分析其工作状态建立了Markov模型。最后以Simulink图形化建模方法完成了相关仿真，通过对系统进行典型故障注入验证了冗余管理算法，仿真结果表明提高系统故障检测覆盖率有利于增强系统可靠性。

Abstract:

The probe into system reliability has been the top issue in the design of spacecraft. The flight control system(FCS), as the core system, will lead to the failure of the whole mission as soon as the fault occurs. To meet the demand of improving the reliability of FCS, the design scheme for triple modular redundancy(TMR) of FCS was put forward based on 1553B Bus. The architecture design of FCS, hardware configuration of the control board, synchronization between three modules and voting method were formulated, then the design strategy of the system was accomplished. The SiP module based on domestic SoC chip was adopted to satisfy the design trend of localization, miniaturization and light weight of FCS. Besides, in order to study the reliability of the scheme, the Markov model was established by analyzing the system working ststes. Finally, the graphical modeling method of Simulink was used to complete the simulation, and the redundant management algorithm was proved by the typical fault injection. Simulation results suggest improving the coverage rate of fault detection is beneficial to increase system reliability.