|Table of Contents|

Research on pressure oscillation transmission characteristics of attitude control engine based on AMESim(PDF)

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

Issue:
2019年03期
Page:
26-32
Research Field:
研究与设计
Publishing date:

Info

Title:
Research on pressure oscillation transmission characteristics of attitude control engine based on AMESim
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;  pressure oscillation;  transfer characteristic;  AMESim simulation
PACS:
V434.23
DOI:
-
Abstract:
When the pressure disturbance passes through the engine liquid path, it will cause the coupling oscillation between the combustion chamber and the supply pipeline, which will lead to the instability of the system.The simulation model of attitude control engine was built on the basis of AMESim software.Under two pressure disturbance input conditions of supply pipeline and combustor, the transmission characteristics of intermediate frequency unstable pressure oscillation were analyzed by calculating the pressure disturbance rate of liquid path.The results show that the pressure disturbance of the supply pipeline increases linearly along downstream, and the pressure disturbance of the combustion chamber decays rapidly upstream.The amplitude of the excited oscillation pressure increases first and then decreases with the increase of the oscillation frequency, and there is a resonance peak.The fuel pipeline has a higher sensitivity to the supply pressure disturbance, while the oxidant pipeline has a higher sensitivity to the pressure disturbance in the combustion chamber.The pressure disturbance has a great influence on the resonance frequency, and the system has strong excitation oscillation and and is less affected by other frequencies.

References:

[1] 张育林, 刘昆, 程谋森.液体火箭发动机动力学理论与应用[M].北京:科学出版社,2005.
[2] 宣智超, 谢恒, 袁宇.某氢氧发动机推力室氢喷嘴烧蚀问题仿真分析[J].火箭推进,2016,42(5):6-11. XUAN Z C, XIE H, YUAN Y.Simulation analysis of hydrogen nozzle ablation problem existing in thrust chamber of a hydrogen oxygen engine[J].Journal of Rocket Propulsion,2016,42(5):6-11.
[3] DE BENEDICTIS M, ORDONNEAU G.High frequency injection coupled combustion instabilities - study of combustion chamber/feed system coupling[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento, California, Reston, Virigina:American Institute of Aeronautics and Astronautics,2006.
[4] NUSCA M.Investigation of Combustion Instability in Small MMH-NTO Liquid Rocket Engines Using CFD:AIAA2010-1518[R].USA:AIAA,2010.
[5] JIN Y I, YOON H G.Study on dynamic responses of a screw-type pressure-swirl injector under low frequency pressure oscillation[J].International Journal of Spray and Combustion Dynamics,2013,5(4):291-308.
[6] CHUNG Y, KIM H, JEONG S, et al.Dynamic characteristics of open-type swirl injector with varying geometry[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia:American Institute of Aeronautics and Astronautics,2015.
[7] KHIL T, CHUNG Y, BAZAROV V G, et al.Dynamic characteristics of simplex swirl injector in low frequency range[J].Journal of Propulsion and Power,2012,28(2):323-333.
[8] 刘上, 刘红军, 孙宏明, 等.液体火箭发动机中频耦合振荡初步研究[J].推进技术,2013,34(1):101-108.
[9] 杨立军, 富庆飞.燃烧室压力振荡对喷嘴出口流量振荡影响分析[J].火箭推进,2008,34(4):6-11. YANG L J, FU Q F.Investigation on the dynamic interaction between injector flow oscillation and combustion chamber pressure oscillation[J].Journal of Rocket Propulsion,2008,34(4):6-11.
[10] 杨立军, 富庆飞.喷嘴对供应系统到燃烧室压力振荡传递幅频特性的影响[J].航空动力学报,2008,23(2):305-310.
[11] 杨立军, 富庆飞.由喷嘴连接的燃烧室到供应系统压力振荡传递过程研究[J].航空动力学报,2009,24(5):1182-1186.
[12] 车学科.液体推进剂供应管道动态特性研究[D].长沙:国防科学技术大学,2005.
[13] 汪广旭, 付秀文, 石晓波, 等.燃烧室非线性压力振荡及其产生机理研究[J].火箭推进,2016,42(2):29-34. WANG G X, FU X W, SHI X B, et al.Study on nonlinear pressure oscillation and its mechanism in combustion chamber[J].Journal of Rocket Propulsion,2016,42(2):29-34.

Memo

Memo:
-
Last Update: 2019-06-30