ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Selection method of measuring parameters for rocket engine based on fault recognition
Received date: 2023-02-02
Revised date: 2023-03-13
Accepted date: 2023-04-21
Online published: 2023-06-27
To address the problem of measuring parameters selection of liquid rocket engines， we propose a model-based method to improve fault recognition and system reliability. The nonlinear and static mathematical model of the engine system is built， the fault feature list metrics of fault recognition， robustness and system reliability of the engine measurement feature subset are then established respectively， and the optimization design is proposed based on the improved multi-objective binary particle swarm optimization （MOBPSO）. With the optimized measuring parameters， the number of distinguishable faults has increased from 9 to 13， the robustness is equivalent to the original layout， and the risk criterion has increased slightly. The important role of the subsystem mixture ratio in fault recognition is further explored and its mechanism analyzed. The method proposed in this paper has a good application value for the selection of measurement characteristics of other complex， closed-loop dynamic systems.
Xiaopu ZHANG , Feng REN , Pengli XU , Zhimin LI , Caihong SU . Selection method of measuring parameters for rocket engine based on fault recognition[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(22) : 128522 -128522 . DOI: 10.7527/S1000-6893.2023.28522
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