燃油系统高空性试飞应用理论分析  

Theoretical Analysis of Altitude Performance Flight Test of Aircraft Fuel System

作　　者：刘志远 夏树丹 任伟[1] Liu Zhiyuan;Xia Shudan;Ren Wei(Chinese Flight Test Establishment,Xi′an 710089,Shaanxi,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《工程与试验》2018年第1期39-42,共4页Engineering and Test

摘　　要：燃油系统的高空性是影响飞机飞行高度的重要因素。在飞行试验中,对高空性的研究是非常必要的。本文从影响高空性的因素出发,通过供油泵的流体力学特性、汽蚀原理以及燃油饱和蒸气压等理论知识,对国军标中燃油系统高空性试飞要求及试飞方法进行理论分析,为试飞工程师在实际试飞过程中优化试飞方法提供参考。Altitude performance of aircraft fuel system is the important factor that determines flight altitude.In flight test,it is necessary for aircraft to study its altitude performance.There are many factors that limit altitude performance.According to the hydrodynamics characteristic of fuel pump,the principle of cavitation and the saturated vapor pressure,the flight test requirements and methods in military standards for the altitude performance of fuel system are analyzed in the paper,which provides reference for the engineers to optimize flight test methods.

关 键 词：燃油系统 高空性 流体力学特性 饱和蒸气压 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]