直升机燃油箱典型飞行姿态下油液晃动仿真研究  

Fuel Tank Slosh Simulation for Helicopter's Typical Flight Attitudes

作　　者：张丽娜[1] ZHANG Lina(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《机械工程师》2019年第1期131-133,共3页Mechanical Engineer

摘　　要：针对某型直升机飞行剖面中的典型飞行姿态,基于FLOW-3D软件,对燃油箱中油液晃动过程进行了仿真,对燃油压力分布、增压泵吸油口布置位置、燃油瞬态重量重心变化、燃油油量传感器布置位置等进行了分析,给出了晃动过程中油液的压力分布云图、油箱油液重心变化情况。该研究结果与方法可以为直升机燃油系统设计提供参考。According to a type of helicopter's some typical flight attitudes in the flight profile,fuel tank slosh simulation is carried out on FLOW-3D software.The fuel pressure distribution,install position of fuel pump inlet,transient weight and center of gravity changes of fuel and fuel quantity sensor install position are analyzed.The fuel pressure nephogram and changes of fuel center of gravity during the sloshing are given out.The research results and methods can be taken as a reference for the design of helicopter fuel system.

关 键 词：直升机 燃油系统 晃动仿真 

分 类 号：V312[航空宇航科学与技术—航空宇航推进理论与工程]