民用飞机惰化系统架构权衡研究

Research on architecture tradeoff of inerting system for civil aircraft

基于单舱惰化冲洗模型理论,采用Matlab语言,针对民用飞机惰化系统设计开发出系统架构权衡分析工具,该工具后台程序除集成气源压力接口数据库、飞行参数自动生成模型和ASM真值表外,还包含根据落地燃油箱氧气浓度对下降阶段大流量模式下NEA最小流量的寻优算法,通过运用该工具,对全燃油箱惰化民机的惰化系统引气增压子系统形式、NEA流量、燃油箱通气形式、燃油箱极限氧气浓度对ASM数量和引气质量流量的影响进行定量研究,全面比较开式通气架构与闭式通气架构下惰化系统的性能特征,为飞机惰化系统架构设计提供一种工程方法参考。

Based on the single cabin inerting flushing model and MATLAB language,A system level performance analysis tool was designed and developed for the civil aircraft fuel tank inerting system.The tool integrates the bleed air source pressure interface database,the automatic generation model of flight parameters and ASM performance data table,and it also includes the optimization algorithm for the minimum NEA flow under large flow mode during descent stage according to the acceptable landing oxygen concentration within the fuel tank.Through the application of this tool,this paper studies the quantitative effect of bleed pressurization form,NEA flow,tank ventilation form,oxygen concentration limit on ASM quantity and bleed air flow for inerting system with full tank inerting,comprehensively compares the performance requirements of the system under open ventilation architecture and closed ventilation architecture,and provides a trade-off method reference for the architecture design of civil aircraft fuel tank inerting system.