|Table of Contents|

Numerical analysis on starting characteristics of attitude control engine based on orthogonal test design method(PDF)

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

Issue:
2019年05期
Page:
38-44
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical analysis on starting characteristics of attitude control engine based on orthogonal test design method
Author(s):
YANG Lintao;  SHEN Chibing
(Science and Technology on Scramjet Laboratory, College of Aerospace Science,National University of Defense Technology, Changsha 410073, China)
Keywords:
attitude control engine;  orthogonal test design method;  starting process;  response characteristics;  AMESim simulation
PACS:
V434.23
DOI:
-
Abstract:
Based on AMESim modular simulation software, a simulation model for the attitude control engine was established.The effect of propellant viscosity, volume of liquid manifold, combustion time delay, injection pressure drop and valve interval time on the starting response characteristics of attitude control engine were analyzed by the orthogonal test design method.The results show that the main influence factors of the response characteristics are combustion time delay, injection pressure drop and valve interval time, and the sensitivity of the valve interval time is the highest.The sensitivity of chamber pressure overshoot to the propellant viscosity is the lowest, and the response time is the least sensitive to the injection pressure drop.The larger combustion time delay, the smaller injection pressure drop and the larger valve interval, the worse engine response performance.Optimizing the injector atomization performance to decrease the combustion time delay, and appropriately increasing the injection pressure drop are helpful to decrease the response time of the attitude control engine.The valve actuation time is as consistent as possible to reduce the response time of starting process.

References:

[1] 毛晓芳, 汪凤山, 杨晓红, 等.小推力双组元姿控发动机性能研究[J].推进技术, 2012, 33(6): 987-990.
[2] 杜大华, 贺尔铭, 薛杰, 等.大推力液体火箭发动机启动冲击响应特性研究[J].西北工业大学学报, 2016, 34(6): 982-989.
[3] 李锋, 何泽夏, 孙百红.液体火箭发动机启动冲击特性研究[J].机械强度, 2009, 31(3): 375-377.
[4] 陈宏玉, 刘红军, 陈建华.补燃循环发动机强迫起动过程[J].航空动力学报, 2015, 30(12): 3010-3016.
[5] 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.
[6] DIMATTEO F, DEROSA M, ONOFRI M.Transientsimulation of the RL-10A-3-3A rocket engine[C]// Space Propulsion Conference.[S.l.]:[s.n.],2012.
[7] DI MATTEO F, DE ROSA M, ONOFRI M.Start-up transient simulation of a liquid rocket engine[C]//47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011.
[8] YAMANISHI N, KIMURA T, TAKAHASHI M, et al.Transient analysis of the LE-7A rocket engine using the rocket engine dynamic simulator(REDS)[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004.
[9] 陈宏玉, 刘红军, 陈建华, 等.补燃循环发动机关机过程仿真研究[J].推进技术, 2016, 37(12): 2219-2225.
[10] 陈新华, 李伟榕.考虑燃烧过程的航天器液体火箭发动机动态特性分析[J].科学技术与工程, 2010, 10(11): 2665-2671.
[11] 郑大勇, 颜勇, 张卫红.氢氧火箭发动机性能敏感性分析[J].火箭推进, 2011, 37(4): 18-23.ZHENG D Y, YAN Y, ZHANG W H.Analysis for performance parameter sensitivity of hydrogen/oxygen rocket engine[J].Journal of Rocket Propulsion, 2011, 37(4): 18-23.

Memo

Memo:
-
Last Update: 2019-10-25