飞行条件下直升机燃油箱冲洗惰化过程理论研究  

Theoretical Study of In-flight Inerting Process in Helicopter Fuel Tank

作　　者：喻成璋 杨小龙[1] 韩杨 谢增[1] YU Chengzhang;YANG Xiaolong;HAN Yang;XIE Zeng(China Helicopter Research and Development Institute,Jingdezhen 3333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2023年第2期39-44,共6页Helicopter Technique

摘　　要：根据组分质量守恒方程以及燃油溶解气体的变化规律,建立了描述飞行条件下直升机燃油箱冲洗惰化过程的数学模型,通过将计算值与A320中央翼油箱的飞行试验数据进行对比,验证了该模型具有较高的计算精度。以民用直升机作为研究对象,基于双流量模式的油箱防爆策略,开展了拟设计惰化系统的飞行性能仿真计算,对影响惰化过程的关键因素进行了分析。其结论可为国产直升机的惰化系统设计提供参考。Based on multicomponent mass conservation equation and function of oxygen evoluting,a mathematical model to describe the inerting process of the helicopter fuel tank on flight condition was set up.Adopting A320 central wing tank as the object of study,the calculating results of the models showed highly accurate with the experimental data published on the foreign literature.With the fuel tank of a dometic helicopter as the research objective,the dual-flow pattern was adopted to suppress fuel tank explosions.This paper peformed the flight performance of proposed inerting system and analyzed the key factors affecting inerting process.The study of this paper provided a useful reference for the design of domestic helicopter fuel tank inerting system.

关 键 词：飞行惰化 燃油箱 防爆 工程计算 

分 类 号：V228.11[航空宇航科学与技术—飞行器设计]