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首页> 外文学位 >Effect of Inductive Coil Geometry on the Operating Characteristics of a Pulsed Inductive Plasma Accelerator.
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Effect of Inductive Coil Geometry on the Operating Characteristics of a Pulsed Inductive Plasma Accelerator.

机译：感应线圈几何形状对脉冲感应等离子体加速器工作特性的影响。

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摘要

The effect of inductive coil geometry on the operating characteristics of a pulsed inductive plasma thruster is investigated analytically and experimentally. Coil inductance is measured as a function of the position of a simulated current sheet and modeled using finite element analysis to develop a two-dimensional semi-empirical inductance relation that is used to expand a circuit-based acceleration model from one to two dimensions. The model includes electromagnetic and gas-dynamic forces but excludes any process to translate radial plasma motion into axial motion. Furthermore a magnetically-impermeable current sheet encompassing all the propellant for a pulse is assumed to form immediately at the start of the pulse and at the surface of the inductive coil. The two-dimensional acceleration model is nondimensionalized, yielding a set of dimensionless performance scaling parameters. Model results indicate that the introduction of radial current sheet motion caused by a conical inductive coil geometry (versus a flat circular plate) increases the axial dynamic impedance parameter at which thrust efficiency is maximized and generally decreases the overall achievable thrust efficiency. Operational characteristics of two thrusters with inductive coils of different cone angles are explored through thrust stand measurements and time-integrated, unfiltered photography. Trends in impulse bit measurements indicate that, in the present configuration, the thruster with the inductive coil possessing a smaller cone angle produced larger values of thrust, in apparent contradiction to results of the model. Areas of increased light intensity in photographs of thruster operation are assumed to qualitatively represent locations of increased current density. Light intensity is generally greater in images of the thruster with the smaller cone angle when compared to those of the thruster with the larger half cone angle for the same operating conditions, and generally decreases in both thrusters for decreasing mass flow rate and capacitor voltage. The location of brightest light intensity shifts upstream for decreasing mass flow rate of propellant and downstream for decreasing applied voltage. Recognizing that there exists an optimum ratio of applied electric field to pressure with respect to breakdown efficiency, this result may indicate that the optimum ratio was not achieved uniformly over the coil face, leading to non-uniform, weak current sheet formation in violation of the model assumption of immediate formation from all injected propellant of a magnetically-impermeable current sheet.
机译：通过分析和实验研究了感应线圈的几何形状对脉冲感应等离子推进器运行特性的影响。线圈电感作为模拟电流表的位置的函数进行测量，并使用有限元分析进行建模以开发二维半经验电感关系，该关系用于将基于电路的加速度模型从一维扩展到二维。该模型包括电磁力和气体动力，但不包括将径向等离子运动转换为轴向运动的任何过程。此外，假定在脉冲开始时以及在感应线圈的表面上立即形成了包含所有用于脉冲的推进剂的不透磁电流层。二维加速度模型是无量纲的，从而产生了一组无量纲的性能缩放参数。模型结果表明，由圆锥形感应线圈几何形状（相对于平坦的圆形板）引起的径向电流薄层运动的引入会增加轴向动阻抗参数，从而使推力效率最大化，并且总体上会降低可实现的总体推力效率。通过推力架测量和时间积分，未经过滤的摄影，探索了具有不同锥角的感应线圈的两个推进器的操作特性。脉冲钻头测量的趋势表明，在本配置中，带有感应线圈且锥角较小的推进器会产生较大的推力值，这与模型结果明显矛盾。假定推进器运行照片中光强度增加的区域定性地表示电流密度增加的位置。与相同工作条件下具有较大半锥角的推进器的图像相比，在具有较小锥角的推进器的图像中，光强度通常更大，并且在两个推进器中通常都会减小光强度，以降低质量流量和电容器电压。最亮光强度的位置向上游移动以降低推进剂的质量流量，向下游移动以降低施加的电压。认识到存在相对于击穿效率的最佳施加电场与压力之比，该结果可能表明，未在线圈表面上均匀地达到最佳比，导致不均匀，薄弱的电流形成，这违反了不可渗透的电流层的所有注入推进剂立即形成的模型假设。

著录项

  • 作者

    Hallock, Ashley Kristin.;

  • 作者单位

    Princeton University.;

  • 授予单位 Princeton University.;
  • 学科 Engineering Aerospace.;Physics Fluid and Plasma.
  • 学位 Ph.D.
  • 年度 2012
  • 页码 94 p.
  • 总页数 94
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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