水下超音速燃气射流推力特性实验研究

王安华; 赵子杰; 刘霄汉; 周标军; 侯典俸; 戴琪

doi:10.12382/bgxb.2025.1083

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水下超音速燃气射流推力特性实验研究

更新时间：2026-04-26

- 水下超音速燃气射流推力特性实验研究
- Experimental Study on Thrust Characteristics of Underwater Supersonic Gas Jets
- 兵工学报 2026年
- 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
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2025.1083
  中图分类号： TJ6
- 收稿：2025-12-09，
  
  网络首发：2026-04-26，
- 稿件说明：
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王安华，赵子杰，刘霄汉，等. 水下超音速燃气射流推力特性实验研究[J/OL]. 兵工学报, 2026(2026-04-26). https://doi.org/10.12382/bgxb.2025.1083.

WANG A H, ZHAO Z J, LIU X H, et al. Experimental study on thrust characteristics of underwater supersonic gas jets[J/OL]. Acta Armamentarii, 2026(2026-04-26). https://doi.org/10.12382/bgxb.2025.1083. (in Chinese)
王安华，赵子杰，刘霄汉，等. 水下超音速燃气射流推力特性实验研究[J/OL]. 兵工学报, 2026(2026-04-26). https://doi.org/10.12382/bgxb.2025.1083. DOI：

WANG A H, ZHAO Z J, LIU X H, et al. Experimental study on thrust characteristics of underwater supersonic gas jets[J/OL]. Acta Armamentarii, 2026(2026-04-26). https://doi.org/10.12382/bgxb.2025.1083. (in Chinese) DOI：

摘要

水下超音速燃气射流在过膨胀状态下引发的大幅值、低频推力振荡，严重制约了水下推进系统的运行稳定性，然而现有研究在真实高温工况及高精细度实验数据方面仍存在显著空白。本文在大型开阔水域环境中开展系统性实验，针对欠膨胀、设计工况及过膨胀3种状态下的固体火箭发动机，实现高频推力信号与高速流场图像的同步采集。实验结果表明，扩张比是决定射流稳定性的关键参量，欠膨胀与设计工况表现出稳定的推力输出与较深的穿透距离，过膨胀工况则呈现出显著的“弛豫振荡”特征，其推力频谱主导频率约为28 Hz；多物理场耦合分析证实，该振荡源于外部流体动力学驱动的“颈缩-鼓胀”周期性形态演化，与燃烧室内部压力波动无关。具体而言，环境水压驱动的射流颈缩导致上游燃气积聚，在喷管出口形成正向压差推力；而惯性主导的过膨胀鼓胀形成低压空腔，产生负向压差推力。所得结果揭示了高温燃气射流推力振荡的内在物理机制，明确了射流失稳的流体力学边界，为水下推进系统的稳定性设计提供了确凿的实验依据。

Abstract

Large-amplitude

low-frequency thrust oscillations induced by over-expanded underwater supersonic gas jets significantly compromise the operational stability of underwater propulsion systems. However

there remains a notable scarcity of high-fidelity experimental data obtained under authentic high-temperature operating conditions in existing literature. To address this gap

a systematic experimental study was conducted in a large-scale unconfined water environment. Synchronous acquisition of high-frequency thrust signals and high-speed flow field imagery was achieved for a solid rocket motor operating under under-expanded

design

and over-expanded conditions.Experimental results indicate that the nozzle expansion ratio is a critical parameter governing jet stability. The under-expanded and design conditions exhibited stable thrust output and deep penetration capabilities. In contrast

the over-expanded condition demonstrated distinct "relaxation oscillation" characteristics

characterized by a dominant spectral frequency of approximately 28 Hz. Coupled multi-physics analysis confirmed that these oscillations originate from a periodic "necking-bulging" morphological evolution driven by external hydrodynamics

independent of internal combustion chamber pressure fluctuations. Mechanistically

ambient-pressure-driven jet necking induces upstream gas accumulation

generating a positive pressure differential thrustat the nozzle exit; conversely

inertia-dominated over-expansion bulging creates a low-pressure cavity

resulting in a negative pressure differential thrust. This study elucidates the underlying physical mechanisms of thrust oscillation in high-temperature gas jets and delineates the hydrodynamic boundaries of jet instability

providing a robust experimental foundation for the stability design of underwater propulsion systems.

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references

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超声速喷管扩张型面对水下喷气推进振荡特性的影响