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An analysis and simulation of launch vehicle separation dynamics including thrust transients.

机译:包括推力瞬变在内的运载火箭分离动力学的分析和仿真。

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摘要

An analysis of the stage separation of a launch vehicle and potential for re-contact is conducted. The launch vehicle with thrust transient and mass offset in the spent stage is assumed; the engine lies recessed at the time of separation within the spent-stage's forward skirt. The potential for and effects of re-contact during separation are investigated. Coordinate systems and the equations of motion are developed. Closed-form analyses are performed for simplified cases. Furthermore, simulations are performed to verify the closed-form solutions, and the differences between simulation results and analytical solutions are discussed.
机译:进行了运载火箭的阶段分离和重新接触的可能性的分析。假定在耗尽阶段具有推力瞬变和质量偏移的运载火箭;分离时,发动机处于凹进级前裙板内。研究了分离过程中重新接触的可能性和影响。建立了坐标系和运动方程。对于简化的情况,将执行封闭式分析。此外,进行仿真以验证封闭形式的解,并讨论了仿真结果与解析解之间的差异。

著录项

  • 作者

    Capps, Charles David.;

  • 作者单位

    The University of Alabama in Huntsville.;

  • 授予单位 The University of Alabama in Huntsville.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.
  • 学位 M.S.
  • 年度 2011
  • 页码 119 p.
  • 总页数 119
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 TS97-4;
  • 关键词

  • 入库时间 2022-08-17 11:44:41

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