Analysis on strength of the orbit and attitude control section body for missile

Sheng Hai Xiang*, Ping Zhang, Shi Peng Li, Shu Zhou Fang

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

Abstract

The for orbit and attitude control section body for missile under multi-loading modes was analyzed by means of NAS-TRAN and PATRAN finite element softwares, and its structure strength with and without reinforcement measures was compared. The calculated results show that safety coefficient of design for the section body is high, and the maximum stress value and the maximum deformation value of the section body with cover reinforcement measures are approximately a half of those without any measures. The test results prove that the calculation analysis method is effective and reliable.

Original languageEnglish
Pages (from-to)350-353
Number of pages4
JournalGuti Huojian Jishu/Journal of Solid Rocket Technology
Volume29
Issue number5
Publication statusPublished - Oct 2006

Keywords

  • Finite element method
  • Orbit and attitude control section body for missile
  • Section body structure
  • Strength analysis

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Xiang, S. H., Zhang, P., Li, S. P., & Fang, S. Z. (2006). Analysis on strength of the orbit and attitude control section body for missile. Guti Huojian Jishu/Journal of Solid Rocket Technology, 29(5), 350-353.