Fault simulation of ducted rocket based on system configuration switch method

被引：0
|
作者：
Wang A. [1 ]
Zeng Q. [2 ]
Zhou Y. [1 ]
机构：
[1] College of Aeronautics and Astronautics, National University of Defense Technology, Changsha
[2] School of Aeronautics and Astronautics, Sun Yat-Sen University, Guangzhou
来源：
Guofang Keji Daxue Xuebao/Journal of National University of Defense Technology | 2019年 / 41卷 / 04期
关键词：
Aircraft engine fault modeling; Ducted rocket; Fault simulation; System configuration switch;
D O I：
10.11887/j.cn.201904012
中图分类号：
学科分类号：
摘要：
In order to comprehensively verify the fault detection algorithm in the ducted rocket rapidly, a simulation platform based on system configuration switch method was built, which can simulate various fault mode for ducted rocket. Based on the simulation platform, the ducted rocket ignite fault model, pressure sensor fault model, device interface model and fault detection algorithm model which have a same interface and system configuration with the aircraft engine controller, etc. were built. Compared with the fault detect result of mathematical model and engine control system under a same fault mode, the fault detection algorithm in the engine control system can be verified rapidly. Taking the fault simulation of nozzleless booster ignition as an example, the modeling, the test, the verification, and the process of analysis were narrated. In addition, it is also applicable to the fault simulation and verification of the shutdown of nozzleless booster, the open of air inlet cover, the ignition of gas generator, and fault tolerant control of gas flow, which has strong universality, and can greatly reduce the time cost on system development and verification, and it has a strong applied value. © 2019, NUDT Press. All right reserved.
引用
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页码：79 / 85
页数：6
相关论文
共 8 条
  • [1] Lyu Z., Xia Z., Liu B., Et al., Review of research on solid fuel scramjet engine, Journal of Aerospace Power, 31, 8, pp. 1973-1984, (2016)
  • [2] Li R., Guo Y., Wu W., Design and verification of simulation platform for aircraft engine sensor fault diagnosis, Computer Measurement and Control, 18, 3, pp. 527-529, (2010)
  • [3] Zhao C., Ye Z., Wang J., Et al., Rapid prototype real-time simulation of turbo-fan engine sensor fault diagnosis, Journal of Aerospace Power, 29, 2, pp. 451-457, (2014)
  • [4] Zhang S., Guo Y., Chen X., Performance evaluation and simulation validation of fault diagnosis system for aircraft engine, Journal of Propulsion Technology, 34, 8, pp. 1121-1127, (2013)
  • [5] Ye S.F., Wang J., Zhang G., Et al., Simulation and fault diagnosis for aviation engine starting system based on SIMULINK, Proceedings of Chinese Automation Congress, (2016)
  • [6] Lyu S., Guo Y., Sun H., Hardware-in-the-loop real-time simulation platform of engine fault diagnosis device, Aeroengine, 43, 3, pp. 43-49, (2017)
  • [7] Wang T., Xue W., Lyu H., Study on sensor fault diagnosis simulation for aircraft engine control system, Computer Simulation, 33, 2, pp. 56-60, (2016)
  • [8] Li Y.P., Li W., The design of the test control system of small piston aircraft engine, Advanced Materials Research, 1061-1062, pp. 912-915, (2015)
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