Simplified Modeling and Model Correction of a Liquid Rocket Engine Nozzle

被引：0
作者：
Liao C. [1 ]
Wang X.-W. [1 ]
Mu P.-G. [2 ]
机构：
[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] Science and Technology on Liquid Rocket Engine Laboratory, Xi’an Aerospace Propulsion Institute, Xi'an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2020年 / 41卷 / 03期
关键词：
Liquid rocket engine; Modal calculation; Model correction; Nozzle; Simplified modeling;
D O I：
10.13675/j.cnki.tjjs.190026
中图分类号：
学科分类号：
摘要：
Nozzle is an important component of liquid rocket engine. Its dynamic characteristics have an impact on the reliability of the whole engine in service. Accurate understanding of nozzle dynamic characteristics is of great significance for response prediction, fault diagnosis and improvement design of liquid rocket engine. An equivalent simplified modeling method that combines model correction based on experimental data is proposed. Firstly, the original geometric model of nozzle was simplified by geometric processing, and the finite element model of nozzle was established. The modal calculation of the finite element model was carried out under free condition. The calculated data were compared with the test data, and then the elastic modulus parameters of the finite element model were modified by the test data. The first nine order modal calculation results and measurement of the modified finite element model of nozzle are obtained. The frequency difference between the first nine order modal calculation results of the modified finite element model of nozzle and the measurement results are less than 5%, and the MAC (Modal Assurance Criterion) is more than 0.8. It shows that this method is a highly efficient and feasible nozzle simplified modeling method, which not only ensures the calculation accuracy but also improves the calculation efficiency. It has important application value for its dynamic characteristics analysis and vibration response prediction. It is also universal for dynamic modeling and analysis of other components of the rocket engine. © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：650 / 655
页数：5
相关论文
共 7 条
  • [1] Fujiwara S., Yumii K., Saguchi T., Et al., Reduction of Tire Groove Noise Using Slot Resonators, Tire Science & Technology, 37, 3, pp. 207-223, (2009)
  • [2] Wang Q., Wang Z., Dong C.Y., Attitude Control of Flexible Launch Vehicle Based on Second-Order Sliding Mode, Journal of System Simulation, 21, 7, (2009)
  • [3] Du F.-P., Tan Y.-H., Chen J.-H., Dynamics of Rocket Engine Structure Based on Substructure Test Modeling, Journal of Propulsion Technology, 36, 10, pp. 1547-1553, (2015)
  • [4] Christopher R., Low Mean Internodal Distance Network Topologies and Simulated Annealing, IEEE Transactions on Communications, 40, 8, pp. 1319-1326, (1992)
  • [5] Baklanov V.S., Low-Frequency Vibro Isolation Mounting of Power Plants for New-Generation Airplanes with Engines of Extra-High Bypass Ratio, Journal of Sound and Vibration, 308, 3-5, pp. 709-720, (2007)
  • [6] Mottershead J.E., Link M., Friswell M.I., The Sensitivity Method in Finite Element Model Updating: A Tutorial, Mechanical Systems & Amp
  • [7] Signal Processing, 25, 7, pp. 2275-2296, (2011)
1