Research on the pressure oscillation characteristics ofdouble pulse solid rocket motor

LIU Wei-kai; HE Guo-qiang; WANG Chun-guang

doi:10.13224/j.cnki.jasp.2015.10.031

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Research on the pressure oscillation characteristics ofdouble pulse solid rocket motor

更新时间：2026-07-07

- Research on the pressure oscillation characteristics ofdouble pulse solid rocket motor
- Vol. 30, Issue 10, Pages: 2553-2560(2015)
- 作者机构：
  
  1. 西北工业大学航天学院燃烧、热结构与内流场重点实验室,西安,710072
  2. 中国航天科技集团公司航天动力技术研究院西安航天动力技术研究所,西安,710025
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2015.10.031
  CLC：
- Published：2015
- 稿件说明：
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刘伟凯, 何国强, 王春光. 双脉冲固体火箭发动机压强振荡特性研究[J]. 航空动力学报, 2015, 30(10): 2553-2560.

doi: 10.13224/j.cnki.jasp.2015.10.031
刘伟凯, 何国强, 王春光. 双脉冲固体火箭发动机压强振荡特性研究[J]. 航空动力学报, 2015, 30(10): 2553-2560. DOI： 10.13224/j.cnki.jasp.2015.10.031.

doi: 10.13224/j.cnki.jasp.2015.10.031 DOI：

摘要

为了研究隔舱消融对双脉冲发动机中燃烧室的压强振荡影响规律

选择隔舱消融几个典型时刻进行研究

运用大涡模拟(LES)方法

对Ⅱ脉冲工作时的发动机流场稳定性进行数值模拟.最后得到了各工况下的压强时间曲线及其快速傅氏变换(FFT)结果.分析表明:由于Ⅱ脉冲工作初期隔舱暴露在流场中产生额外扰动

以及隔舱级间通道形成狭窄通道的加速作用

是导致边界层分离而引起障碍涡脱落的主要因素.点火初期

双脉冲发动机易发生轻微压强振荡.随隔舱消融

整个流场在发动机工作中、后期逐渐趋于平稳.

Abstract

In order to reveal the relationship between the melting of pulse separation device (PSD) and the pressure oscillation

several melting moments were selected for research. Large eddy simulation (LES) was carried out for the numerical simulation of II pulse flow field

and the pressure-time curve and fast Fourier transformation (FFT) results were obtained successfully.The analysis results show that the additional disturbance in the flow field generated by opening PSD when the Ⅱ pulse is working

and the acceleration of interstage narrow channel

are the main factors to obstacle vortex shedding caused by boundary layer separation. In the early ignition

the double pulse motor (DPM)is prone to slight pressure oscillation. With the PSD melting

the whole flow field becomes more and more stabilized.

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引用格式：王庆宇,刘琪麟,赖焕新.高亚声速喷流近场的流-声关联［J］.航空动力学报,2020,35(12):2532-2542.WANG Qingyu,LIU Qilin,LAI Huanxin.Flow-acoustics correlations in near-fields of high subsonic jet［J］.Journal of Aerospace Power,2020,35(12):2532-2542.Flow-acoustics correlations in near-fields of high subsonic jet

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Related Institution

National Key Laboratory of Science and Technology on Liquid Rocket Engines，Xi'an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation

Academy of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation

Beijing Aerospace Institute for Metrology and Measurement Technology， China Academy of Launch Vehicle Technology， China Aerospace Science and Technology Corporation

School of Mechanical Engineering， University of Shanghai for Science and Technology

Research Institute of Aero-engine,Beijing University of Aeronautics and Astronautics

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