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首页> 外文期刊>Journal of Spacecraft and Rockets >Force and Moment Measurements on a Free-Flying Capsule in a Shock Tunnel
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Force and Moment Measurements on a Free-Flying Capsule in a Shock Tunnel

机译：冲击隧道中自由飞行胶囊的力和力矩测量

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摘要

Experiments to measure the forces and moments acting on a blunted-cone capsule model are conducted in the High Enthalpy Shock Tunnel Gottingen. A free-flying arrangement is employed, whereby the model is initially suspended by weak threads that are detached by the arrival of the flow, allowing unrestrained flight during the steady test time. High-speed shadowgraphy is used to capture the model motion. Induced forces and moments are measured using both internally mounted accelerometers and visualization-based tracking techniques. Improvements to the visualization-based techniques allow the elimination of several previously identified sources of error. Drag, lift, and pitching-moment coefficients are derived over a range of angles of attack up to 6 deg, and excellent agreement is obtained between the techniques. Results are also compared with those from numerical simulations, with agreement found to lie within the experimental error for the drag and pitching coefficients but slightly outside for the lift coefficients. The precision of the visualization-based results is such that uncertainty in the freestream conditions is the dominant source of experimental error in the drag coefficient, and it becomes comparable to or larger than the standard error in the lift and pitching accelerations at the maximum angle of attack tested.
机译：在高焓冲击隧道哥廷根中进行了测量作用在钝锥胶囊模型上的力和力矩的实验。采用自由飞行装置，由此模型最初由弱螺纹悬挂，该弱螺纹由于流动的到来而分离，从而允许在稳定的测试时间内不受限制地飞行。高速阴影照相法用于捕获模型运动。感应力和力矩使用内部安装的加速度计和基于可视化的跟踪技术进行测量。对基于可视化技术的改进允许消除多个先前确定的错误源。阻力，升力和俯仰力矩系数是在高达6度的迎角范围内得出的，并且在这两种技术之间获得了极好的一致性。结果也与数值模拟的结果进行了比较，发现阻力和俯仰系数在实验误差范围内，而升力系数在实验误差范围内。基于可视化结果的精度使得自由流条件下的不确定性是阻力系数实验误差的主要来源，并且在最大倾角下，其升力和俯仰加速度的标准误差变得可比或大于标准误差。攻击测试。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2018年第2期|403-414|共12页
  • 作者

    Laurence S. J.; Butler C. S.; Schramm J. Martinez; Hannemann K.;

  • 作者单位

    Univ Maryland, Dept Aerosp Engn, 3179 Glenn L Martin Hall, College Pk, MD 20742 USA;

    Univ Maryland, Dept Aerosp Engn, 3179 Glenn L Martin Hall, College Pk, MD 20742 USA;

    German Aerosp Ctr, DLR, Spacecraft Dept, Inst Aerodynam & Flow Technol, Bunsenstr 10, D-37073 Gottingen, Germany;

    German Aerosp Ctr, DLR, Spacecraft Dept, Inst Aerodynam & Flow Technol, Bunsenstr 10, D-37073 Gottingen, Germany;

  • 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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