流体喉部推力调节特性实验

郭常超; 于新宇; 李博; 谢侃; 魏志军; 王宁飞

doi:10.13224/j.cnki.jasp.2015.04.029

流体喉部推力调节特性实验

doi: 10.13224/j.cnki.jasp.2015.04.029

1. 北京理工大学宇航学院, 北京 100081;
2. 中国航天科技集团公司北京航天动力研究所, 北京 100076

详细信息

作者简介:
郭常超(1989-),男,重庆人,博士生,主要从事航空宇航推进理论与工程研究.E-mail:gccbit@126.com

通讯作者:
谢侃(1982-),男,湖南冷水江人,讲师,博士,主要从事航空宇航推进理论与工程研究.E-mail:xiekan@bit.edu.cn

中图分类号: V23
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出版历程
- 收稿日期: 2014-11-21
- 刊出日期: 2015-04-28

Experiment on thrust adjustment characteristics of fluidic nozzle throat

1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
2. Beijing Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Beijing 100076, China

摘要

摘要: 采用空气与水作为二次流工质,进行流体喉部的冷流实验,研究了固体火箭发动机流体喉部的推力调节特性.分析了不同二次流工质、注射方式,注射流量下的推力响应时间、扼流性能、推力偏角和推力效率.实验结果表明:注射液态二次流推力响应时间更短;扼流性能、推力偏角与二次流的注射位置及注射角度有关,且随流量比的增大而增大;相同的流量比下,气态二次流的推力性能要比液态二次流的效果更好,但提供相同的流量比,液态二次流需要压比更小,且流量比的调节范围更大.
- 固体火箭发动机 /
- 流体喉部 /
- 二次流 /
- 响应时间 /
- 推力矢量
Abstract: A cold-flow test research of fluidic nozzle throat was performed using the gas and water as secondary flow medium to study the thrust adjustment characteristics of fluidic nozzle throat of solid rocket motor. The influence of different secondary flow mediums, injection ways and injection mass flow rates on thrust response time, choke performance, thrust angle and thrust efficiency were studied. The experimental results show that the thrust response time is shorter using liquid secondary flow; the choke performance and thrust angle are related to injection positions and injection angle of secondary flow, and increase with increasing mass flow rate ratio; under the same mass flow rate ratio, thrust performance by using gaseous secondary flow is better than that by liquid secondary flow; but liquid secondary flow needs smaller pressure ratio and larger mass flow rate ratio adjustment range when the same mass flow rate ratio is given.
- solid rocket motor /
- fluidic nozzle throat /
- secondary flow /
- response time /
- thrust vector

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参考文献(18)

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