一种基于有限单元法的弹箭时变模态参数快速预示方法

余磊; 马清华; 王智毅; 李泽阳

doi:10.15892/j.cnki.djzdxb.2025.06.001

弹箭与制导学报 >

2025 , Vol. 45 >Issue 6: 971 - 977

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.001

学术文章

一种基于有限单元法的弹箭时变模态参数快速预示方法

余磊 ^,¹^,² ,
马清华 ¹^,² ,
王智毅 ¹^,² ,
李泽阳 ¹^,²

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¹ 陆空基信息感知与控制全国重点实验室, 陕西西安 710065
² 西安现代控制技术研究所, 陕西西安 710065

余磊(1990—),男,高级工程师,博士。Email:bit_yulei@foxmail.com。

收稿日期: 2024-06-13

网络出版日期: 2026-01-24

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A Fast Prediction Method for Time-Varying Modal Parameters of Missile and Rocket Based on Finite Element Method

YU Lei ^,¹^,² ,
MA Qinghua ¹^,² ,
WANG Zhiyi ¹^,² ,
LI Zeyang ¹^,²

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¹ National Key Laboratory of Land and Air Based Information Perception and Control,Xi’an 710065, Shaanxi, China
² Xi’an Modern Control Technology Research Institute,Xi’an 710065, Shaanxi, China

Received date: 2024-06-13

Online published: 2026-01-24

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摘要

大型弹箭系统模态参数的获取手段一般为有限元分析与地面振动试验。由于无法模拟飞行状态下的系统时变特征,通常需要基于若干特征工况对系统进行有限元建模或地面振动试验,最终通过数值插值法得到系统飞行模态频率,反复的建模分析与地面试验过程费时费力,资源消耗较大。本文基于集中质量-梁模型,采用有限单元法建立了一种弹箭时变模态参数快速预示方法,该方法引入时变的质量矩阵、刚度矩阵、阻尼矩阵对系统时变动力学模型进行正向建模,进而快速给出系统的时变模态频率参数。该方法采用某远程制导火箭的地面振动试验数据以及飞行遥测数据进行了验证,结果表明该方法能够可靠地模拟系统时变模态参数,有效解决了时变系统仿真繁琐的痛点,基于该方法得到的时变动力学响应数据对天地模态一致性分析、载荷辨识等动力学反问题具有重要意义。

关键词： 制导火箭弹; 模态分析; 有限元方法; 时变系统

本文引用格式

余磊 , 马清华 , 王智毅 , 李泽阳 . 一种基于有限单元法的弹箭时变模态参数快速预示方法[J]. 弹箭与制导学报, 2025 , 45(6) : 971 -977 . DOI: 10.15892/j.cnki.djzdxb.2025.06.001

Abstract

The modal parameters of large-scale missile and rocket systems are generally obtained through finite element analysis and ground vibration tests.Due to the inability to simulate the time-varying characteristics of the system under flight conditions,it is usually necessary to conduct finite element modeling or ground vibration tests based on several characteristic conditions,and finally obtain the flight modal frequency through numerical interpolation.The repeated modeling and ground testing process is time-consuming and laborious.This article presents a fast prediction method for time-varying modal parameters of missile and rocket,which is based on the concentrated mass beam model and finite element method.This method introduces time-varying mass matrix,stiffness matrix,and damping matrix to describe the time-varying system,which can quickly provide the time-varying modal frequency parameters of the system.This method has been validated through ground vibration test and flight test,the results show that this method can reliably simulate the time-varying modal parameters of the system,effectively solving the pain points of the tedious simulation of time-varying systems.Moreover,the time-varying dynamic response data obtained based on this method can be used for dynamic inverse problems such as the modal consistency analysis and load identification.

Key words： guided rocket; modal analysis; finite element method; time-varying system

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