The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine

Xuechen XI; Anqi WANG; Shuzhen NIU; Pengfei YANG

doi:10.12382/bgxb.2024.0171

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The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine

更新时间：2025-09-25

- The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine
- Acta Armamentarii Vol. 46, Issue 8, Pages: 240171(2025)
- 作者机构：
  
  1. 山西警察学院治安系, 山西太原 030401
  2. 北京理工大学空天科学与技术学院, 北京 100081
  3. 中国科学院力学研究所空天飞行高温气动全国重点实验室(筹), 北京 100190
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2024.0171
  CLC：
- Received：11 March 2024，
  
  Published Online：28 August 2025，
  
  Published：31 August 2025
- 稿件说明：
移动端阅览
Xuechen XI, Anqi WANG, Shuzhen NIU, et al. The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine[J]. Acta Armamentarii, 2025, 46(8): 240171.
DOI：

Xuechen XI, Anqi WANG, Shuzhen NIU, et al. The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine[J]. Acta Armamentarii, 2025, 46(8): 240171. DOI： 10.12382/bgxb.2024.0171.

摘要

为了探明前体压缩方式及压缩程度对斜爆轰发动机推力性能的影响规律

针对马赫数10、海拔35km的飞行工况

采用理论分析的手段

研究1道、2道和3道斜激波以及压缩角度对氢气-空气斜爆轰发动机推力性能的影响。研究结果显示

压缩级数的增加能够显著提升斜爆轰发动机的推力性能;在压缩角度2°~24°范围内

燃料比冲随着1级压缩角度的增加呈现出先增大后减小的变化趋势

2级和3级压缩角度的增加能够持续地提升燃料比冲

并延迟推力性能极值点的出现。通过分析进气压缩级数对进气道出口、掺混段出口和燃烧室出口气流参数的影响

发现这一现象主要在于1级楔面压缩角度的增加导致进气道出口气流温度快速上升

限制了爆轰燃烧的增压能力

而多级压缩能够获得更高的燃烧产物压力和速度

从而提升推力性能并降低总压损失。

Abstract

The influences of forebody compression methods and compression levels on the thrust performance of oblique detonation engine (ODE) are studied.The effects of 1-

and 3-stage oblique shocks and compression angles on the thrust performance of hydrogen-air ODE under flight conditions of Mach number 10 and altitude 35km are examined through theoretical analysis.The results indicate a significant enhancement in thrust performance with an increase in the number of compression stages.Within the range of compression angles from 2° to 24°

the fuel specific impulse exhibits an initial increase followed by a decrease with the increase in the compression angle of the 1st stage

while the increases in the angles of the 2nd and 3rd compression lead to a continuous improvement in fuel specific impulse

thus delaying the appearance of peak thrust performance.Analysis of the impact of inlet compression stages on the total pressure at the outlet of inlet duct

the exit of mixing section

and the exit of combustion chamber reveals that the increase in the compression angle of the 1st stage wedge leads to a rapid rise in the outlet airflow temperature of inlet duct

limiting the pressure-gain capability of detonation combustion.Conversely

the multi-stage compression achieves higher combustion product pressure and velocity

thereby enhancing the thrust performance and reducing the total pressure loss.

关键词

Keywords

references

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