摘要
针对民机燃油箱通气特性对惰化系统架构的影响开展定量研究,基于飞机燃油箱惰化过程单舱模型,建立惰化系统架构自动寻优方法,并开发相应计算软件,以冲压恢复系数作为燃油箱通气特性表征参数,给出四种民机燃油箱通气特性定义。以宽体机型为例,完成不同通气特性及不同飞行总体参数下惰化系统架构关键参数计算,包括:空气分离器(ASM)数量、引气量、落地后燃油箱气相空间氧浓度等。研究结果表明:(1)给定飞行参数情况下,油箱压力脉动越剧烈,惰化系统体量越大,引气量越大。相对恒定冲压情况,随机脉动导致引气量增加47.1%,ASM数量增加47.1%。(2)给定通气特性情况下,飞行总体参数影响较小。巡航高度由35000 ft提升至44000 ft,ASM数量不变;环境温度由−40℃提升至26.7℃,ASM数量降低28.2%;马赫数由0.75提升至0.85,ASM数量增加2.9%。为惰化系统设计提供了理论依据,可应用于工程分析,支持型号研制。
To conduct quantitative research on the influence of fuel tank ventilation characteristics on the inerting system architecture of civil aircraft,this study establishes an automatic optimization method for the inerting system architecture based on a single-cabin model of the aircraft fuel tank inerting process and develops corresponding calculation software.Using the stamping recovery coefficient as a characterization parameter for fuel tank ventilation characteristics,this study defines four types of fuel tank ventilation characteristics for civil aircraft.Taking widebody aircraft models as an example,the key parameters of the inerting system architecture are calculated under different ventilation characteristics and overall flight parameters,including the number of air separators,the volume of air drawn,and the oxygen concentration in the fuel tank vapor space after landing.The research findings indicate that:1)Under given flight parameters,more intense fuel tank pressure pulsation results in a larger inerting system volume and greater air intake volume.Compared to the constant ramming scenario,random pulsation increases the air intake volume by 47.1% and the number of ASMs by 47.1%.2)Given the ventilation characteristics,the overall flight parameters have a relatively minor impact.Specifically,when the cruising altitude increases from 35000 ft to 44000 ft,the number of ASMs remains unchanged.When the ambient temperature rises from -40℃ to 26.7℃,the number of ASMs decreases by 28.2%.When the Mach number increases from 0.75 to 0.85,the number of ASMs increases by 2.9%.This study provides a theoretical basis for the design of inerting systems and can be applied to engineering analysis,supporting the development of future models.
作者
张瑞华
江华
薛勇
ZHANG Ruihua;JIANG Hua;XUE Yong(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)
出处
《民用飞机设计与研究》
2026年第1期104-114,共11页
Civil Aircraft Design & Research
关键词
可燃性
压力脉动
惰化
燃油箱
氧浓度
flammability
pressure pulsation
inerting
fuel tank
oxygen concentration
