高速飞行器的连续旋转爆震推进技术

师迎晨; 张任帅; 计自飞; 王兵

doi:10.7638/kqdlxxb-2021.0231

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高速飞行器的连续旋转爆震推进技术

专栏——内外流一体化技术 | 更新时间：2026-05-28

- 高速飞行器的连续旋转爆震推进技术
- Rotating detonation propulsion technology for high-speed aircrafts
- 空气动力学学报 2022年40卷第1期页码：101-113
- 作者机构：
  
  1. 清华大学航天航空学院,北京,100084
  2. 中国航空发动机集团沈阳发动机研究所,沈阳,110015
- 作者简介：
  
  师迎晨（1999-），男，辽宁沈阳人，博士，研究方向：航空宇航推进理论与工程. E-mail：shi-yc21@mails.tsinghua.edu.cn
  王兵*，教授，研究方向：空天动力及飞行器，多相流与燃烧空气动力学. E-mail：wbing@tsinghua.edu.cn
- 基金信息：
  
  国家自然科学基金（51676111，NSAF-U1730104）
- DOI：10.7638/kqdlxxb-2021.0231
  中图分类号： V231.2+2
- 纸质出版：2022
- 稿件说明：
移动端阅览
师迎晨, 张任帅, 计自飞, 等. 高速飞行器的连续旋转爆震推进技术[J]. 空气动力学学报, 2022, 40(1): 101−113.

SHI Yingchen, ZHANG Renshuai, JI Zifei, et al. Rotating detonation propulsion technology for high-speed aircrafts[J]. 2022, 40(1): 101-113.
师迎晨, 张任帅, 计自飞, 等. 高速飞行器的连续旋转爆震推进技术[J]. 空气动力学学报, 2022, 40(1): 101−113. DOI： 10.7638/kqdlxxb-2021.0231

SHI Yingchen, ZHANG Renshuai, JI Zifei, et al. Rotating detonation propulsion technology for high-speed aircrafts[J]. 2022, 40(1): 101-113. DOI： 10.7638/kqdlxxb-2021.0231.

摘要

吸气式高速飞行器具有重要的战略价值，高性能的推进装置始终是高速飞行器领域的核心问题。基于连续旋转爆震构建的推进系统，与当前基于布雷顿循环构建的推进系统相比，具有显著的性能优势，可以弥补当前推进系统造成的“推力陷阱”问题，有望助力高速飞行器取得长远发展。本文总结了连续旋转爆震燃烧过程与分析模型，以及基于连续旋转爆震构建的推进系统的性能优势与研究进展。进一步，针对连续旋转爆震冲压发动机，讨论了本质非定常燃烧室对发动机进气道与尾喷管的设计要求与需求，介绍了进气道抵抗压力波反传的措施，并进行了数值分析，证明了相关措施的可行性。最后展望了采用基于连续旋转爆震构建的推进系统的发展前景。

Abstract

High-performance propulsion technology is one of the core issues for high-speed aircrafts which are of important strategic value. The "thrust trap" problem in current propulsion systems based on the Brayton cycle can be avoided by the rotation detonation. Consequently

the rotating detonation propulsion technology has significant advantages and is expected to help high-speed aircrafts achieve long-term development. To this end

this article summarizes the rotation detonation combustion process and analysis models. The performance advantages and research progress of propulsion systems based on the rotation detonation are introduced as well. Furthermore

the design requirements of the intake and exhaust systems for rotating detonation ramjets by taking the unsteady combustion into effect are discussed. Feasible measures to suppress the back propagation of pressure waves in the inlet are validated through numerical simulations. Finally

prospects of propulsion systems based on the rotation detonation are proposed.

关键词

Keywords

references

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