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Feasibility and Performance of Atmospheric-Breathing Propulsion for Mars Descent

机译：火星下降的大气呼吸推进器的可行性和性能

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摘要

Analysis was performed to assess the impact of atmospheric-breathing supersonic retropropulsion as a technology solution for Mars descent. Vehicle models were developed for three architectures, employing an atmospheric-breathing engine for both descent and terminal maneuvers, an atmospheric-breathing engine for descent and rocket engine for the terminal maneuver, and a fully rocket propulsive vehicle. Investigations into design constraints showed the inlet area to dictate convergence for the all atmospheric-breathing architecture. These vehicles were limited by oxidizer ingestion for the terminal maneuver and the reduced propulsive descent timeline. Optimal configurations preferred lower-thrust, lower-propellant-usage designs, which were better able to mitigate the mass penalty of the low thrust-to-weight engine. The terminal rocket architectures were instead limited by rocket thrust, which compensated for marginal deceleration during descent. Optimal configurations tended toward large atmospheric-breathing engine performance over high thrust terminal rocket engines because of the favorable fuel usage. Among all architectures considered, the solely atmospheric-breathing vehicles had the best mass performance, with reductions for all component masses with respect to the terminal rocket engine. The terminal rocket architecture did not exhibit significant performance increase over fully rocket vehicles. This study shows that atmospheric-breathing propulsion has promise for improving Mars descent.
机译：进行了分析以评估大气呼吸超音速逆向推进作为火星下降的技术解决方案的影响。针对三种架构开发了车辆模型，分别采用了降落和末尾机动的大气呼吸发动机，降落和末尾机动的大气呼吸发动机以及火箭推进器。对设计约束的研究表明，进气口面积决定了所有大气呼吸建筑的收敛性。这些车辆受到氧化剂摄入的限制，以进行最终机动并减少推进后裔的时间表。最佳配置首选低推力，低推进剂使用设计，这种设计能够更好地减轻低推重比发动机的质量损失。相反，终端火箭的结构受到火箭推力的限制，从而弥补了下降过程中的边际减速度。由于有利的燃料使用，与高推力终端火箭发动机相比，最佳配置趋于使大气呼吸的发动机具有更大的性能。在所有考虑的架构中，仅具有大气呼吸功能的飞行器具有最佳的质量性能，相对于终端火箭发动机，所有部件的质量都有所减少。终端火箭的结构没有表现出比全火箭飞行器显着的性能提升。这项研究表明，大气呼吸推进有望改善火星下降。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2018年第2期|346-355|共10页
  • 作者

    Gonyea Keir C.; Braun Robert D.; Auslender Aaron H.;

  • 作者单位

    Georgia Inst Technol, Sch Aerosp Engn, Atlanta, GA 30332 USA;

    Univ Colorado, Coll Engn & Appl Sci, Boulder, CO 80309 USA;

    NASA, Langley Res Ctr, Hyperson Airbreathing Prop Branch, Hampton, VA 23666 USA;

  • 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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