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液体火箭发动机三轴向虚拟振动试验技术研究

韩帅 曹亚文 邓长华 穆朋刚 霍世慧 李斌潮 薛杰

火箭推进2018,Vol.44Issue(6):68-74,7.
火箭推进2018,Vol.44Issue(6):68-74,7.

液体火箭发动机三轴向虚拟振动试验技术研究

Research on test technology for three-axial virtual vibration of liquid rocket engine

韩帅 1曹亚文 1邓长华 1穆朋刚 1霍世慧 1李斌潮 1薛杰1

作者信息

  • 1. 西安航天动力研究所, 陕西 西安 710100
  • 折叠

摘要

Abstract

The vibration test is an important part for the structure reliability evaluation and force enviorment adaption verification of the liquid rocket engine. In comparison with the uniaxial vibration test, the three-axial vibration test is more realistic to simulate the actual stress of the product. The study on the virtual three-axial vibration test is worth significantly on predicting the dynamic response of a liquid rocket engine, guiding design optimization for the structure, and modifying the unialxial vibration test input spectrum for three-axial vibration test. Aimed at the vibration problem of the liquid rocket engine, a virtual vibration testing system for three-axial vibration table was built up by the control method and finite element simulation technology of the three-axial vibration table. The joint simulation dynamics modeling combining with a certain product and vibration table model was conducted on the basis of the Patran finiteelement platform. The test conditions of sine vibration and random vibration test were taken as loading boundary for dynamics response analysis to solve the three-axial vibration using Nastran software. By comparison and modification with the actual vibration test results, the accurate models of the three-axial vibration table and the product as well as accuracy control method were obtained, which can provide a virtual test method for the structural vibration response prediction and weekness identification of the liquid rocket engine.

关键词

液体火箭发动机/三轴向振动台/正弦振动/随机振动

Key words

liquid rocket engine/three-axial shaking table/sine vibration/random vibration

分类

航空航天

引用本文复制引用

韩帅,曹亚文,邓长华,穆朋刚,霍世慧,李斌潮,薛杰..液体火箭发动机三轴向虚拟振动试验技术研究[J].火箭推进,2018,44(6):68-74,7.

基金项目

装发部预研项目(41410040202) (41410040202)

火箭推进

OACSTPCD

1672-9374

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