微型拉瓦尔喷管的流体仿真分析和优化
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摘要
采用Fluent软件对微型模块化液化气微推进系统的拉瓦尔喷管进行了流体仿真,得到了喷管各个尺寸因素对有效比冲和推力的影响曲线关系,并给出了喷管的最终优化结果。喷管有五个尺寸因素:入口直径、喉部直径、出口直径、收缩段长度和扩张段长度。其中,喉部直径越大,推力越大,有效比冲越小;出口直径越大,推力和有效比冲越大;收缩段长度较小时,对有效比冲影响较大,对推力几乎无影响;入口直径和扩张段长度对推力和有效比冲的影响很小可忽略。
The modular liquefied gas micro-propulsion system of Laval nozzle was simulated by using FLUENT software,and got each size of nozzle thrust and effective specific impulse,and gave the optimized results of nozzle. The nozzle has five sizes:inlet diameter,throat diameter,outlet diameter,contraction length and expansion length. Among them,the greater the throat diameter,the larger the thrust,the smaller the effective specific impulse; the greater the outlet diameter,the larger the thrust and effective specific impulse; when the contraction length is small,it affects the effective specific impulse,and almost has no effects on thrust; the effects of inlet diameter and expansion length are very small to be ignored.
The modular liquefied gas micro-propulsion system of Laval nozzle was simulated by using FLUENT software,and got each size of nozzle thrust and effective specific impulse,and gave the optimized results of nozzle. The nozzle has five sizes:inlet diameter,throat diameter,outlet diameter,contraction length and expansion length. Among them,the greater the throat diameter,the larger the thrust,the smaller the effective specific impulse; the greater the outlet diameter,the larger the thrust and effective specific impulse; when the contraction length is small,it affects the effective specific impulse,and almost has no effects on thrust; the effects of inlet diameter and expansion length are very small to be ignored.
引文
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[2]尤政,张高飞,任大海.MEMS微推进技术的研究[J].纳米技术与精密工程,2004,2(2):1-8.
[3]尤政,林杨,张高飞.基于微机电系统的微推进发展新趋势[J].中国航天,2005(6):12-15.
[4]晋晓伟,童飞,马键,等.一种用于微纳卫星的丙烷微推进系统[J].火箭推进,2012,38(1):1-4.
[5]韩先伟,周军,唐周强,等.微型推进系统技术方案研究[J].火箭推进,2005,31(1):1-7.
[6]陆永华,魏文权,邵飞翔,等.拉瓦尔喷管小推力测量系统数值计算研究[J].机电工程,2016,33(10):1189
[7]李云鹏.机动飞行器冷喷气推进系统设计及地面试验研究[D].哈尔滨:哈尔滨工业大学,2013:34-57.
[8]王定军,宋会玲,刘伟.冷气推进器流场仿真和分析[J].火箭推进,2010,2(36):38-39.
[9]于红勇,韩远鹏,干昌浩.冷气推进系统内弹道计算方法研究[J].中国高新技术企业,2012(10):9-10.
[10]周伟勇,张育林.基于有效比冲的小卫星冷气推进系统设计[J].字航学报,2010,31(1):173-178.
[11]张成军.实验设计与数据处理[M].北京:化学工业出版社,2009:8-19.
[12]李云雁,胡传荣.试验设计与数据处理[M].北京:化学工业出版社,2008:231.