|Table of Contents|

Simulation study on start-up processes of a multi-startup turbopump-fed rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2019年05期
Page:
17-24
Research Field:
研究与设计
Publishing date:

Info

Title:
Simulation study on start-up processes of a multi-startup turbopump-fed rocket engine
Author(s):
PU Guangrong;  SHAN Lei;  ZHAO Xiaohui;  CHEN Hongyu
(Xi’an Aerospace Propulsion Institute, Xi’an 710100, China)
Keywords:
turbopump-fed;  liquid rocket engine;  multi-startup;  start-up characteristics;  simulation analysis
PACS:
V430
DOI:
-
Abstract:
By adopting a refillable start-tank as the starting system in a upper stage liquid rocket engine, the multi-startup of the turbopump-fed engine has been realized, but the engine start-up process is more complicated than the gun-type startup mode with powder starter.In order to understand the working characteristics of the multi-startup process, a dynamic simulation model was established to achieve the performance parameters of the multi-startup process, which was based on the MWorks platform using Modelica language.The simulation results include the effect of startup box pressure, propellant consumption of startup box and main starting parameters on the startup process.The propellant consumption of startup box is much less than the design volume of startup box during every startup.During the startup process, the parameter variation shows the remarkable characteristics with three platforms and is “extrusion start-refill-steady state work”.In addition, the engine can start up normally within a wide range of startup box pressure.The results of engine hot firing test verify the rationality of the engine startup sequence setting and the effect of parameter settings on startup process.

References:

[1] YAMANISHI N,KIMURA T, TAKAHASHI M, et al.Transient analysis of the LE-7A rocket engine using the rocket dynamic simulator(REDS):AIAA 2004-3850[R].USA:AIAA,2004.
[2] DURTESTE S.A transient model of the VINCI cryogenic upper stage rocket engine:AIAA 2007-5531[R].USA:AIAA,2007.
[3] MATTEO F D, ROSA M D.Start-up transient simulation of a liquid rocket engine: AIAA 2011-6032 [R].USA:AIAA, 2011.
[4] 赵建军, 丁建完, 周凡利, 等.Modelica语言及其多领域统一建模与仿真机理[J].系统仿真学报, 2006, 18(S2): 570-573.
[5] 张小平.补燃循环发动机起动过程仿真研究[J].火箭推进, 2003, 29(3): 18-21.ZHANG X P.Simulation study on starting process of a supplementary combustion cycle engine [J].Journal of Rocket Propulsion, 2003, 29(3): 18-21.
[6] 杨永强, 刘红军, 徐浩海, 等.补燃循环发动机强迫起动研究[J].火箭推进, 2011, 37(2): 14-18.YANG Y Q, LIU H J, XU H H, et al.Research on forced start-up of staged combustion engine[J].Journal of Rocket Propulsion, 2011, 37(2): 14-18.
[7] 张卫红, 李玲玲, 颜勇,等.大推力氢氧发动机起动瞬态特性仿真研究[J].航天推进与动力, 2004(4): 7-12.
[8] 肖立明, 罗巧军.膨胀循环发动机起动过程研究[J].火箭推进, 2007, 33(1): 7-11.XIAO L M, LUO Q J.Investigation on start-up process of expander cycle liquid propellant rocket engine[J].Journal of Rocket Propulsion, 2007, 33(1): 7-11.
[9] 尘军, 王桁.高压补燃氢氧发动机系统动态仿真[J].航天推进与动力, 2008(2): 15-21.
[10] 刘上, 王艺杰, 程晓辉, 等.小推力泵压式发动机自身起动过程仿真分析[J].火箭推进, 2016, 42(4): 7-13.LIU S, WANG Y J, CHENG X H, et al.Simulation of self start-up process for low thrust pump-fed rocket engine[J].Journal of Rocket Propulsion, 2016, 42(4): 7-13.
[11] 张金容, 汪亮.液体火箭发动机起动过程的动态仿真计算[J].低温工程, 2008(2): 22-27.
[12] 黄仕启, 刘登丰.上面级发动机瞬态工作过程的模块化建模仿真与工程应用[J].航天推进与动力, 2012(3):39-35.
[13] 苏龙斐, 张黎辉, 潘海林.卫星推进系统发动机启动过程数值仿真[J].航空动力学报, 2005, 20(4): 698-701.
[14] 陈宏玉, 刘红军, 刘上.推进剂管路充填过程的数值模拟[J].航空动力学报, 2013, 28(3): 561-566.
[15] 黄其殷, 王幸果, 刘上, 等.液氧/煤油发动机起动箱仿真与试验研究[J].火箭推进, 2015, 41(3): 21-26.HUANG Q Y, WANG X G, LIU S, et al.Simulation and test study on starting box of LOX/kerosene rocket engine[J].Journal of Rocket Propulsion, 2015, 41(3): 21-26.
[16] 陈阳, 张振鹏, 瞿骞, 等.液体火箭发动机试验台贮箱增压系统数值仿真[J].航空动力学报, 2007, 22(1): 96-101.
[17] 陈宏玉, 刘红军.液体火箭发动机瞬态特性模型库及其应用[C]//中国宇航学会液体专业委员会2013年学术会议论文集.安康:中国宇航学会液体专业委员会, 2013.

Memo

Memo:
-
Last Update: 2019-10-25