Experimental Study of Solid Fuel-rich Gas Rotating Detonation Engine

WANG Jinping; LI Baoxing; BAI Qiaodong; HAN Jiaxiang; WENG Chunsheng

doi:10.12382/bgxb.2025.0397

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Experimental Study of Solid Fuel-rich Gas Rotating Detonation Engine

更新时间：2026-04-24

- Experimental Study of Solid Fuel-rich Gas Rotating Detonation Engine
- Acta Armamentarii Vol. 47, Issue 3, Pages: 250397(2026)
- 作者机构：
  
  南京理工大学瞬态物理全国重点实验室，江苏南京 210094
  西安近代化学研究所，陕西西安 710065
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2025.0397
  CLC： V231.22
- Received：22 May 2025，
  
  Online First：25 December 2025，
  
  Published：2026-03
- 稿件说明：
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WANG Jinping, LI Baoxing, BAI Qiaodong, et al. Experimental Study of Solid Fuel-rich Gas Rotating Detonation Engine[J]. Acta Armamentarii, 2026, 47(3): 250397.
DOI：

WANG Jinping, LI Baoxing, BAI Qiaodong, et al. Experimental Study of Solid Fuel-rich Gas Rotating Detonation Engine[J]. Acta Armamentarii, 2026, 47(3): 250397. DOI： 10.12382/bgxb.2025.0397.

摘要

固体推进剂具有较高的能量密度和可靠性，有望成为旋转爆轰发动机的优选燃料。为了解决其在贫氧状态下燃烧生成的富燃燃气与空气起爆困难的问题，采用空桶型燃烧室以增强燃料的能量释放程度，成功实现了固体富燃燃气与纯空气的旋转爆轰燃烧，并详细分析了旋转爆轰波的传播特性及模态演变规律。实验结果表明：预爆轰管点火后经过了约296.6 ms成功建立旋转爆轰波，其在燃烧室内以单波模态沿顺时针方向传播（燃烧室出口视角），稳定工作阶段的传播速度达到了1439.1 m/s±16.6 m/s，平均峰值压力约为0.37 MPa；除二次点火时刻速度波动较大外，稳定传播过程中波速的相对标准差均小于11%；研究结果可大大推动固体富燃燃气旋转爆轰冲压发动机的工程化应用。

Abstract

Solid propellants have high energy density and superior reliability

and are expected to become a preferred fuel for rotating detonation engine. To address the challenge of initiating between the fuel-rich gas generated by combustion of solid propellants under oxygen-deficient conditions and air

a hollow combustor is utilized to enhance the energy release of fuel. Successful rotating detonation combustion of solid fuel-rich gas and pure air is achieved

and the propagation characteristics and mode evolution pattern of rotating detonation wave are analyzed in detail. The experimental results show that the rotating detonation wave is successfully established after approximately 296.6 ms after the ignition of the pre-detonator

and it propagates in a single wave mode along the clockwise direction（Combustor exit perspective）in the combustor

achieving a propagation velocity of 1439.1 m/s±16.6 m/s and an average peak pressure of approximately 0.37 MPa in the stable operating phase. Except for a significant velocity fluctuation during the secondary ignition

the relative standard deviation of wave velocity in the stable propagation process is less than 11% . The study results can significantly advance the engineering application of solid fuel-rich gas rotating detonation ramjet engines.

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references

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