Numerical Simulation and Performance Analysis on Start Process of Missile Turbojet Engine Windmill

YANG Xin-yi;SHEN Wei;LIU Hai-feng;DONG Ke-hai;WANG Yong-hua

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  • Sponsored by: China Association for Science and Technology (CAST)

    Editor-In-Chief: Xu Yida

    ISSN 1000-1093

    　

  • Hosted By: China Ordnance Society

    Published By: Acta Armamentarii

    CN 11-2176/TJ

Acta Armamentarii, a Chinese monthly journal, was first published in 1979. The journal is supervised by China Association for Science and Technology, sponsored by China Ordnance Society，and edited and published by Editorial Board of Acta Armamentarii. The Journal is included in all important domestic databases，and also collected by Engineering Index (EI, USA), Chemical Abstracts (CA, USA), Science Abstracts (SA, UK）, Abstract Journal (AJ, Russia), and Current Bibliography on Science and Technology(CBST).Acta Armamentarii has been selected into the journal Of Ordnance Science and Technology (Weapons Industry) Field Of High Quality Scientific and Technological Periodical Classification Catalogue (2022 edition), ranking T1, and the journal of Automotive Engineering Field of High Quality Scientific and technological Periodical classification Catalogue, ranking T2.
Acta Armamentarii ›› 2011, Vol. 32 ›› Issue (1) : 37-44. DOI: 10.3969/j.issn.1000-1093.2011.01.007
Paper

Numerical Simulation and Performance Analysis on Start Process of Missile Turbojet Engine Windmill

  • YANG Xin-yi， SHEN Wei， LIU Hai-feng， DONG Ke-hai， WANG Yong-hua
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Abstract

A new simulation strategy was proposed for the start process of missile turbojet engine windmill according to its characteristic. The simulation consists of two phases: the windmill process before ignition and the acceleration process after ignition. The former is simulated using radial basis function networks (RBFN)，and the latter which model is a set of nonlinear equations is solved using particle swarm optimization (PSO) algorithm. The introduction of PSO helps to solve the divergence problem of nonlinear equations caused by traditional iteration method when the initial condition is far from real solution. The results are in agreement with test data, which shows that the presented model has a higher accuracy. The start processes at the different ignition times were simulated, and the results were analyzed synthetically. The analysis shows how the ignition time affects the acceleration performance of the engine windmill start, which provides a theoretical foundation for igniting time optimization.

Key words

propulsion system of aviation & aerospace / missile propulsion / turbojet engine / windmill / moving least square / particle swarm optimization / acceleration performance

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YANG Xin-yi， SHEN Wei， LIU Hai-feng， DONG Ke-hai， WANG Yong-hua. Numerical Simulation and Performance Analysis on Start Process of Missile Turbojet Engine Windmill. Acta Armamentarii. 2011, 32(1): 37-44 https://doi.org/10.3969/j.issn.1000-1093.2011.01.007

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