Research on Real-Time Process Monitoring Technology and System for High-Speed Turbopump

Article Preview

Abstract:

Turbopump is a high-fault-rate component in Liquid Rocket Engine (LRE). The research on real-time process monitoring technology and system for turbopump is vital to increase the reliability and safety of LRE. In this paper, three real-time process monitoring algorithms for turbopump were studied firstly, on the basis of monitoring parameters selection and multiple domain feature extraction. Then, the real-time monitoring system realized by means of PXI (PCI eXtensions for Instrumentation) controller was introduced. And, aiming at the shortage of the previous system, the real-time process monitoring system based on DSP (Digital Signal Processor) for turbopump was studied to realize higher computing speed, which could conduce to extract multiple domain features and run manifold real-time monitoring algorithms. The new system could also satisfy the small-sized requirement in engine flying state.

You might also be interested in these eBooks

Info:

Periodical:

Key Engineering Materials (Volumes 413-414)

Pages:

463-469

Citation:

Online since:

June 2009

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2009 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] T. Coffin: Specialized Data Analysis of SSME and Advanced Propulsion System Vibration Measurements. NASA Contractor Technology Reports N94-29868 (1994).

Google Scholar

[2] T.R. Fiorucci, D.R. Lakin II and T.D. Reynolds: Advanced Engine Health Management Applications of the SSME Real-time Vibration Monitoring System. AIAA-2000-3622 (2000).

DOI: 10.2514/6.2000-3622

Google Scholar

[3] F. Jue and F. Kuck: Space Shuttle Main Engine (SSME) Options for the Future Shuttle. AIAA-2002-3758 (2002).

DOI: 10.2514/6.2002-3758

Google Scholar

[4] M. Dvidson and J. Stephens: Advanced Health Management System for the Space Shuttle Main Engine. AIAA-2004-3912 (2004).

Google Scholar

[5] G.J. Xie, N.Q. Hu and G.J. Qin: Journal of Propulsion technology, Vol. 26 (2005), p.540.

Google Scholar