热水火箭发动机喷管性能的影响因素  

Influential factors of nozzle performance of hot water rocket motor

作　　者：孙巍伟[1] 魏志军[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2015年第4期992-998,共7页Journal of Aerospace Power

摘　　要：为了更好地了解影响热水火箭发动机喷管性能的因素,分别对不同参数条件下喷管内流场进行数值模拟.重点研究不同初始条件如不同初始压力、初始气体体积分数及过冷度和不同喷管结构如不同扩张比、收敛半角及扩张半角对推力的影响规律,计算结果表明:初始压力越大,推力越大;随着初始气体体积分数增大,推力会有一个先增大后减小的过程;热水火箭发动机内部初始温度越接近于饱和温度,推力越大;随着扩张比的增加,推力会有一个先增大后减小的过程;收敛半角对推力影响不大;扩张半角越大,推力越小.In order to learn the influential factors of nozzle performance of hot water rocket motor deeper,numerical simulation of the flow field in the nozzle were performed at different parameter conditions.The impact rules of different initial conditions such as pressure,vapor volume fraction,supercooling and different nozzle structures such as expansion ratio,converging half-angle and expansion half-angle to the thrust were investigated.The calculating results show that：the greater the initial pressure,the greater the thrust;as the initial vapor volume fraction increases,thrust has a process of increase first and then decrease;thrust is larger when the initial temperature of hot water rocket motor is closer to the saturation temperature;thrust has a process of increase first and then decrease with the increasing of expansion ratio;the impact of converging half-angle to the thrust is minor;the greater the expansion half-angle,the smaller the thrust.

关 键 词：热水火箭发动机 闪蒸 相变 喷管性能 流场 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]