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弹箭与制导学报 >

2023 , Vol. 43 >Issue 1: 104 - 110

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2023.01.015

固体火箭发动机试验模态分析

  • 张永亮 1 ,
  • 贾亮 1 ,
  • 狄文斌 2 ,
  • 任冬辉 1 ,
  • 韩铭 1
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  • 1 北京强度环境研究所,北京 100076
  • 2 上海宇航系统工程研究所,上海 201109

张永亮(1986—),男,高级工程师,硕士,研究方向:结构动力学。

收稿日期: 2022-02-26

  网络出版日期: 2025-02-01

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Modal Test and Analysis of Solid Rocket Motor

  • ZHANG Yongliang 1 ,
  • JIA Liang 1 ,
  • DI Wenbin 2 ,
  • REN Donghui 1 ,
  • HAN Ming 1
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  • 1 Beijing Institute of Structure and Environment Engineering, Beijing 100076, China
  • 2 Shanghai Institute of Astronautical Systems Engineering,Shanghai 201109,China

Received date: 2022-02-26

  Online published: 2025-02-01

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摘要

针对某大型分段式固体火箭发动机试验模态分析,试验结果出现了直观“不平衡”的扭转振型,通过数据分析结合试验模型的可观测性状和固体发动机的结构形式,认为药柱的弹性特性影响是主要因素。由于固体火箭发动机是密封充压结构,用于保护药柱,因此不能对药柱粘贴测点进行验证测试。为此建立固体发动机对比仿真模型,并基于试验数据对仿真模型进行了修正,然后按照模态试验的激振方式进行谐响应分析。分析结果验证了直观“不平衡”的扭转振型,证明了药柱的弹性特性是导致上述现象的原因。当固体火箭发动机直径增加,装药量也将大幅增加,低刚度和粘弹性特性固体推进剂的弹性特性将对整体弹性特性的影响将不可忽视,因此针对大型固体火箭发动机提出了试验模态分析药柱的测量和激振要求。

关键词： 固体火箭发动机; 分段式; 试验模态分析; 药柱

本文引用格式

张永亮 , 贾亮 , 狄文斌 , 任冬辉 , 韩铭 . 固体火箭发动机试验模态分析[J]. 弹箭与制导学报, 2023 , 43(1) : 104 -110 . DOI: 10.15892/j.cnki.djzdxb.2023.01.015

Abstract

The experimental modal analysis of a large segmented solid rocket motor was carried out. The intuitive “unbalanced” torsional vibration mode appeared in the test was analyzed. Through data analysis combined with the observable assembly of the test model and the structural form of the solid motor. It was considered that the main factor is the elastic property of the propellant. Due to the solid rocket motor is usually sealed and pressurized, which is used to protect the propellant, it is impossible to verify the test point of propellant sticking. Therefore, the comparative simulation model of solid motor was established. The simulation model was modified based on the experimental data. The harmonic response was analyzed according to the excitation scheme of modal test. The analysis results verified the intuitive “unbalanced”torsional vibration mode, and proved that the elastic characteristics of grain is the cause of the above phenomenon. Therefore, with the increase of SRM size, the propellant of SRM will increase greatly. The elastic properties of solid propellants with low stiffness and viscoelastic properties can not be ignored. At the same time, the measurement and excitation requirements of grain for experimental modal analysis of large solid rocket motor are also proposed.

Key words： solid rocket motor; large segmented; test modal analysis; propellant

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