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弹箭与制导学报 >

2014 , Vol. 34 >Issue 6: 47 - 50

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2014.06.012

导弹与制导技术

基于有限元算法的惯导缓冲减振机构设计

  • 程文娟 ,
  • 白真 ,
  • 何宁
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  • 1 中国兵器工业第203研究所,西安 710065
    2 陕西理工学院,陕西汉中 723000

程文娟(1988-),女,陕西渭南人,硕士研究生,研究方向:飞行器结构设计。

收稿日期: 2014-02-03

  网络出版日期: 2025-05-30

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Optimized Design on Vibration-isolation of Inertial Navigation by Using Finite Element Method

  • CHENG Wenjuan ,
  • BAI Zhen ,
  • HE Ning
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  • 1 No. 203 Research Institute of China Ordnance Industries, Xi'an 710065, China
    2 Shaanxi University of Technology, Shaanxi Hanzhong 723000, China

Received date: 2014-02-03

  Online published: 2025-05-30

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摘要

针对某型导弹弹载惯导装置缓冲减振机构形式及布局进行设计。采用有限元中的瞬态动力学算法,分析在发动机点火瞬间,弹载惯导装置在经过缓冲减振机构缓冲隔振后的冲击响应情况,并通过地面点火试验对设计方案进行验证。通过仿真计算和实验验证可见该方案在发动机点火瞬间具有缓冲减振功效,缓冲效率高达65%。

关键词： 惯导减振; 冲击响应; 有限元分析

本文引用格式

程文娟 , 白真 , 何宁 . 基于有限元算法的惯导缓冲减振机构设计[J]. 弹箭与制导学报, 2014 , 34(6) : 47 -50 . DOI: 10.15892/j.cnki.djzdxb.2014.06.012

Abstract

Structure and layout of onboard buffer damping device were designed for a certain type of missile inertial navigation system. By using the transient dynamics algorithm of the finite element method, the impact response of missile inertial navigation system at the moment of engine ignition was analyzed, after a buffer was installed on it for isolating the vibration, and the design was validated by ground firing test. Through simulation and experimental validation of the design concept, the effect by using a buffer to reduce vibration during engine ignition is significant; the efficiency is up to 65%.

Key words： vibration-isolation of inertial navigation; shock response; finite element analysis

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参考文献

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