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首页> 外文期刊>Journal of Spacecraft and Rockets >Aerothermal-Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Descent
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Aerothermal-Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Descent

机译：火箭发射的Mach 8超燃冲压发动机的气热结构分析：下降

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摘要

This paper reports on the methodology and results of a weak-coupled aerothermal-structural analysis on the exoatmospheric and descent phase of the Mach 8 SCRAMSPACE flight-test engine. The passively cooled short-duration test engine was manufactured from common engineering materials including a 5 mm-thick aluminum aeroshell, an 8-10 mm aluminum inlet and combustion chamber assembly, and a 4-8 mm-thick carbon-phenolic thrust nozzle. Aerothermal heating and aerodynamic pressure on the external and internal flowpaths, including pulsed (5 Hz) fueling and combustion, were first solved using two- and three-dimensional computational fluid dynamics models. Results from these simulations where then used as boundary conditions to a three-dimensional transient thermal-structural finite element analysis model. The external aeroshell was found to maintain temperatures and stresses to within acceptable limits. Elevated surface temperatures along the internal flowpath were observed; however, the median stresses remained below material failure limits. This analysis indicates that, although the structure weakens and becomes more plastic, the vehicle integrity was maintained until the specified end of the experimental window. Results from this study demonstrate that, with careful design, thin-walled structures made from common engineering materials are suitable for short-duration hypersonic airbreathing flight-test engines without the need of active-cooling technology.
机译：本文报告了对Mach 8 SCRAMSPACE飞行试验发动机的大气和下降阶段进行的弱耦合空气热结构分析的方法和结果。被动冷却式短时试验发动机由常见的工程材料制造而成，包括5毫米厚的铝质航空器壳体，8到10毫米铝质进气口和燃烧室组件以及4毫米至8毫米厚的碳酚推力喷嘴。首先使用二维和三维计算流体动力学模型解决了外部和内部流动路径上的气热加热和空气动力压力，包括脉冲式（5 Hz）加油和燃烧。这些模拟的结果随后被用作三维瞬态热结构有限元分析模型的边界条件。发现外部机壳将温度和应力保持在可接受的范围内。观察到沿内部流动路径的表面温度升高；但是，中值应力仍低于材料破坏极限。该分析表明，尽管结构变弱并变得更具塑性，但车辆的完整性一直保持到实验窗口的指定末端。这项研究的结果表明，经过精心设计，由普通工程材料制成的薄壁结构适用于短时高超音速呼吸飞行测试发动机，而无需主动冷却技术。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2018年第2期|501-517|共17页
  • 作者

    Capra Bianca R.; Brown L. M.; Boyce R. R.;

  • 作者单位

    Queensland Univ Technol, Sch Chem Phys & Mech Engn, Fac Sci & Engn, 2 George St,GPO Box 2434, Brisbane, Qld 4001, Australia;

    Univ New South Wales Canberra, Canberra, ACT 2600, Australia;

    Univ New South Wales Canberra, Sch Engn & IT, Canberra, ACT 2600, Australia;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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