热水火箭发动机喷管性能的影响因素

孙巍伟; 魏志军; 王宁飞

doi:10.13224/j.cnki.jasp.2015.04.028

热水火箭发动机喷管性能的影响因素

doi: 10.13224/j.cnki.jasp.2015.04.028

北京理工大学宇航学院, 北京 100081

详细信息

作者简介:
孙巍伟(1987-),男,河南辉县人,博士生,研究方向为热水火箭发动机.E-mail:332915161@bit.edu.cn

中图分类号: V439
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- 被引次数: 0
出版历程
- 收稿日期: 2013-11-26
- 刊出日期: 2015-04-28

Influential factors of nozzle performance of hot water rocket motor

School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

摘要

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.
- 热水火箭发动机 /
- 闪蒸 /
- 相变 /
- 喷管性能 /
- 流场
Abstract: 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.
- hot water rocket motor /
- flash evaporation /
- phase change /
- nozzle performance /
- flow field

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参考文献(15)

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