Volume 37 Issue 1
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WANG Yingpeng, XU Yihua, SUN Haijun, FENG Xiping. Optimization design for nozzle contour of rocket engine based on response surface method[J]. Journal of Aerospace Power, 2022, 37(1): 214-224. doi: 10.13224/j.cnki.jasp.20210004
Citation: WANG Yingpeng, XU Yihua, SUN Haijun, FENG Xiping. Optimization design for nozzle contour of rocket engine based on response surface method[J]. Journal of Aerospace Power, 2022, 37(1): 214-224. doi: 10.13224/j.cnki.jasp.20210004
shu

Optimization design for nozzle contour of rocket engine based on response surface method

doi: 10.13224/j.cnki.jasp.20210004
  • 1.

    Jiangxi Key Laboratory of Micro Aeroengine，School of Aircraft Engineering， Nanchang Hangkong University，Nanchang 330063，China

  • 2.

    Science and Technology on Combustion，Internal Flow and Thermo-Structure Laboratory，Northwestern Polytechnical University，Xi'an 710072，China

  • Received Date: 2021-01-05
  • Publish Date: 2022-01-28
    Abstract
  • Based on the known gas parameters of a certain rocket engine，the performance of nozzle with convergent section designed by Witoszynski，bicubic curve，quintic curve and axis shifting method based on Witoszynski was analyzed on a comparative basis.Better performance of nozzle was obtained by axis shifting method.The nozzle contour parameters （initial arc radius of arc segment，outlet half angle，length diameter ratio of expansion section） were calculated and analyzed by single variable method.The results showed that the nozzle outlet thrust decreased with the increase of the initial expansion arc radius and outlet half angle； with the increase of the length diameter ratio of the convergent section，the length diameter ratio of the expansion section and the expansion angle，the nozzle outlet thrust first increased and then decreased.Due to the interact phenomenon of the influence of the parameters of each contour，the response surface method （RSM） was used to optimize the parameters of nozzle contour in order to comprehensively consider the influence of various parameters on nozzle performance.The results showed that the length of the performance of nozzle contour obtained by RSM was reduced by 3.40% with the increase of thrust.

     

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