Calculation and analysis by modular modeling for frequency characteristics of a LOX/LH2 rocket engine

被引：0
|
作者：
Zhang W. [1 ]
Zhang J. [1 ]
Zhang N. [1 ]
机构：
[1] Beijing Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Beijing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2022年 / 37卷 / 06期
关键词：
approximate model; coupled system; frequency characteristics; modular modeling; stability analysis;
D O I：
10.13224/j.cnki.jasp.20210660
中图分类号：
学科分类号：
摘要：
In order to analyze the frequency characteristics of a LOX/LH2 rocket engine，an engine linearized dynamic model with main and subsidiary systems coupled was developed，including pipelines described by one-dimensional distributed parameter model，combustion components described by adiabatic flow model considering entropy wave and pumps components were described by model considering cavitation. The transcendental functions in thermodynamic component models and distributed parameter models were expressed by rational approximation. After establishing modular simulation model in Simulink， a frequency sweep was conducted to obtain the frequency characteristics， and hot test data was implemented in validation. The result showed that the modular simulation library is user-friendly， and is capable of analyzing the low to medium frequency characteristics of the engine system. Under the excitation of gas pulsation， the engine produced the frequency response of 10 and 165 Hz in main system and 124 and 204 Hz in subsidiary system. The calculated characteristics frequency showed better accuracy while considering the rotation speed feedback. The stability of the engine system was improved while increasing the local resistance of the pipeline before the pump or increasing the pressure drop of the gas generator injection. © 2022 BUAA Press. All rights reserved.
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页码：1336 / 1344
页数：8
相关论文
共 18 条
  • [1] LIU Shang, LIU Hongjun, CHEN Jianhua, Et al., Dynamical characteristics of flow regulator in pump feed system[J], Jounals of Rocket Propulsion, 40, 2, pp. 29-35, (2014)
  • [2] XUE Wei, HU Hui, WU Xiaoping, Thrust closed-loop control of the large scale expandable liquid rocket propulsion[J], Computer Measurement and Control, 27, 6, pp. 90-94, (2019)
  • [3] SPANYER K L., Results of calculations from theoretical equations pertaining to POGO transfer functions, (1980)
  • [4] OPPENHEIM B W, RUBIN S., Advanced POGO stability analysis for liquid rockets[J], Journal of Spacecraft and Rocket, 30, 3, pp. 2050-2062, (1993)
  • [5] WANG Qingwei, Stability of large - loop system coupled between attitude control and POGO for liquid rocket, (2015)
  • [6] LI Bin, DU Dahua, ZHANG Guitian, Et al., Research on the low frequency characteristics of LOX/kerosene staged combustion cycle engine, Journal of Aerospace Power, 24, 5, pp. 1187-1191, (2009)
  • [7] CHEN Qifeng, LIU Kun, ZHANG Yulin, Frequency characteristics computation of liquid rocket engine based on distributed parameter model, Journal of Aerospace Power, 16, 1, pp. 44-48, (2001)
  • [8] WANG Jue, ZHANG Zhenpeng, Research on frequency characteristics of LOX/LH<sub>2</sub> rocket engine, Journal of Aerospace Power, 23, 12, pp. 2341-2345, (2008)
  • [9] LIU Shang, LIU Hongjun, CHEN Jianhua, Et al., Investigation on oxidizer-rich preburner feed system coupled stability[J], Journal of Propulsion Technology, 34, 11, pp. 1448-1458, (2013)
  • [10] LIU Shang, LIU Hongjun, SUN Hongming, Et al., Preliminary study of medium frequency coupled oscillation in liquid rocket engine, Journal of Propulsion Technology, 34, 1, pp. 101-108, (2013)
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