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

Yingpeng WANG; Yihua XU; Haijun SUN; Xiping FENG

doi:10.13224/j.cnki.jasp.20210004

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

Rocket Engine | 更新时间：2025-04-07

- Optimization design for nozzle contour of rocket engine based on response surface method
- Journal of Aerospace Power Vol. 37, Issue 1, Pages: 214-224(2022)
- 作者机构：
  
  1.南昌航空大学飞行器工程学院江西省微小航空发动机重点实验室，南昌 330063
  2.西北工业大学燃烧、热结构与内流场重点实验室，西安 710072
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210004
  CLC：
- 稿件说明：
移动端阅览
Yingpeng WANG, Yihua XU, Haijun SUN, et al. Optimization design for nozzle contour of rocket engine based on response surface method[J]. Journal of Aerospace Power, 2022, 37(1): 214-224.
DOI：

Yingpeng WANG, Yihua XU, Haijun SUN, et al. 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.

摘要

针对已知某型火箭发动机的燃气参数，对比了维托辛斯基、双三次、五次曲线及基于维托辛斯基的移轴法设计的收缩段型面喷管性能，其中移轴法得到喷管性能较优；采用单一变量法计算分析了喷管型面参数（初始扩张段圆弧半径、扩张段出口半角、扩张段长径比、扩张段扩张角以及收缩段长径比）对喷管性能影响规律，喷管出口推力随着初始扩张段圆弧半径以及出口半角的增大而减小；随着收缩段长径比、扩张段长径比以及扩张角的增大，喷管出口推力先增大后减小。由于各型面参数的影响关系存在着耦合现象，为了综合考虑各参数对喷管性能影响，采用响应面法（RSM）对喷管型面各参数进行优化设计，结果表明：RSM所得到的型面喷管在推力增加的基础上，长度减小了3.40%。

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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references

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