摘要
针对高升力系统中襟缝翼控制计算机的余度架构进行基础技术研究,设计了一种可靠性高、可抑制共模/共域故障、成本合适的新的余度架构。提出了襟缝翼控制计算机的通道结构与驱动分系统结构紧耦合,分析了3种主流余度模型,从而确定了襟缝翼控制计算机余度架构的通道结构和支路结构:新余度架构采用双通道模式,满足驱动分系统的驱动方式需求,每个通道内部将襟翼和缝翼功能进行物理隔离,功能通道内部由2个支路构成命令-监控结构。同时设计了新余度架构的工作方式,并使用广义随机Petri网分析了新余度架构的可靠性。
The basic technical research is carried out on the margin architecture of the FSECU in the high lift system,and a new margin architecture with high reliability,suppression of common mode/same area failures,and appropriate cost is designed.The channel structure of the FSECU is proposed to be tightly coupled with the structure of the drive subsystem,and three mainstream margin models are analyzed to determine the channel structure and branch structure of the FSECU margin architecture:The new margin architecture adopts a 2 channel mode to meet the requirements of the drive mode of the drive subsystem.The flap and slat functions are physically isolated inside each channel,and the command monitoring structure is formed by two branches inside the functional channel.The working method of the new surplus architecture is also designed,and the reliability of the new margin architecture is analyzed using GSPN.
作者
白晨
马子飞
边庆
BAI Chen;MA Zi-fei;BIAN Qing(Xi′an Aeronautics Computing Technique Research Institute,AVIC,Xi′an 710000,China)
出处
《航空计算技术》
2023年第2期92-95,共4页
Aeronautical Computing Technique
基金
航空科学基金项目资助(2020Z069031001)。
