基于正交试验的固体火箭超燃冲压发动机优化设计

冯滢; 付文娟; 胡振坤; 唐勇; 赵马杰; 石保禄

doi:10.12382/bgxb.2024.0820

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基于正交试验的固体火箭超燃冲压发动机优化设计

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- 基于正交试验的固体火箭超燃冲压发动机优化设计
- Optimization Design of Solid Rocket Scramjet Engine Based on Orthogonal Experiments
- 兵工学报 2025年46卷第9期页码：240820
- 作者机构：
  
  1. 北京理工大学空天科学与技术学院, 北京 100081
  2. 北京动力机械研究所, 北京 100074
  3. 北京理工大学(珠海), 广东珠海 519088
- 作者简介：
  
  * shibaolu@bit.edu.cn
- 基金信息：
  
  国家自然科学基金项目(U20B2018);国家自然科学基金项目(U21B2096);国家自然科学基金项目(U23B6009)
- DOI：10.12382/bgxb.2024.0820
  中图分类号：
- 收稿：2024-08-20，
  
  网络出版：2025-09-24，
  
  纸质出版：2025-09-30
- 稿件说明：
移动端阅览
冯滢, 付文娟, 胡振坤, 等. 基于正交试验的固体火箭超燃冲压发动机优化设计[J]. 兵工学报, 2025,46(9):240820.

Ying FENG, Wenjuan FU, Zhenkun HU, et al. Optimization Design of Solid Rocket Scramjet Engine Based on Orthogonal Experiments[J]. Acta Armamentarii, 2025, 46(9): 240820.
冯滢, 付文娟, 胡振坤, 等. 基于正交试验的固体火箭超燃冲压发动机优化设计[J]. 兵工学报, 2025,46(9):240820. DOI： 10.12382/bgxb.2024.0820.

Ying FENG, Wenjuan FU, Zhenkun HU, et al. Optimization Design of Solid Rocket Scramjet Engine Based on Orthogonal Experiments[J]. Acta Armamentarii, 2025, 46(9): 240820. DOI： 10.12382/bgxb.2024.0820.

摘要

为研究固体火箭超燃冲压发动机中硼颗粒点火和燃烧特性以及补燃室结构对发动机燃烧性能的影响

编写表征硼颗粒点火和燃烧过程的用户自定义程序

分析超燃冲压发动机中凝相颗粒的燃烧释能动态特征。基于正交设计试验方法

分别从颗粒特征参数和发动机结构角度出发

分析硼颗粒粒径、燃气入射角和凹腔深度以及两两之间交互作用对发动机燃烧效率的影响规律。研究结果表明:通过极差和方差分析

各因素对发动机燃烧效率影响大小排序为硼颗粒粒径>粒径与燃气入射角度的交互作用>燃气入射角>凹腔深度>燃气入射角和凹腔深度的交互作用>粒径与凹腔深度的交互作用

最终确定的最优组合燃烧效率达77.01%;硼颗粒粒径对于固体火箭冲压发动机燃烧效率具有高度显著影响

粒径与燃气入射角的交互作用的影响不容忽视。

Abstract

The effects of the ignition and combustion characteristics of boron particles in a solid rocket scramjet engine and the combustor structure on the combustion performance of engine are studied.A user-defined function program for characterizing the ignition and combustion processes of boron particles is written

and the dynamic characteristics of combustion energy release of condensed-phase particles in a ramjet is analyzed.Furthermore

based on the orthogonal design experimental method

the effects of boron particle size

gas injection angle and cavity depth

as well as their interactions on engine combustion efficiency are analyzed from the perspectives of particle characteristics and engine structure.Through range and variance analyses

the results indicate that the factors influencing the engine combustion efficiency are ranked as follows:boron particle size > interaction between particle size and gas injection angle > gas injection angle > cavity depth > interaction between gas injection angle and cavity depth > interaction between particle size and cavity depth.The optimal combination achieves a combustion efficiency of 77.01%.The boron particle size has a significant effect on the combustion efficiency of solid rocket scramjet engine

and the interaction between particle size and gas injection angle cannot be ignored.

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Keywords

references

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