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首页> 外文会议>1st International conference on green propellant for space propulsion >REUSABLE HYDRO-CARBON BOOSTER STAGES AS A REPLACEMENT FOR LARGE SOLID ROCKET MOTORS
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REUSABLE HYDRO-CARBON BOOSTER STAGES AS A REPLACEMENT FOR LARGE SOLID ROCKET MOTORS

机译：可重复使用的油气增强阶段，可替代大型固体火箭发动机

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摘要

This paper investigates different types of reusable first stages using hydro-carbon propulsion designed for a near term application with heavy lift launchers. The attached reference expendable space transportation system is a future Ariane 5 with cryogenic core and upper stage, but skipped solid rocket boosters. The design of the so called liquid fly-back boosters (LFBB) is restricted here to the incorporation of hydro-carbon-LOX rocket motors already under development or in operation.rnThe analyzed lay-out-variants of the reusable vehicle include attached single as well as dual LFBB-configurations. Catamaran type double fuselage stages are regarded to evaluate the potential in reducing the unsymmetrical thrust load of one side mounted boosters. Beside their primary use to boost heavy lift GTO missions, a second task may be covered by the same vehicle to accelerate the upper stages of small and medium launchers. The additional requirements in designing the same reusable launch vehicle for at least two different missions are studied.rnThe investigation includes trajectory simulations and optimizations for ascent. Return to the launch site by the LFBB is regarded, concerning the propellant requirements and the loads on the vehicle. Different booster shapes are generated by CAD for a preliminary aerodynamic sizing, dimensioning, and mass estimation. The paper includes a comparison of performance, and quantified exhaust data of the liquid fly-back booster configurations with large solid rocket motors. The relevant rocket engine figures of performance, mass, reusability, and throttling capability are presented.
机译：本文研究了使用烃类推进器的不同类型的可重复使用的第一阶段，该推进器设计用于重型举升装置的近期应用。随附的参考消耗性太空运输系统是具有低温核心和上层级的未来Ariane 5，但没有使用固体火箭助推器。所谓的液体反激式助推器（LFBB）的设计仅限于结合已经在开发或运行中的碳氢化合物LOX火箭发动机。以及双重LFBB配置。双体船型双机身阶段被认为可评估减少一侧安装的助推器的非对称推力载荷的潜力。除了主要用于提升重型GTO任务外，同一辆车还可能承担第二项任务，以加速中小型发射器的上层阶段。研究了为至少两个不同的任务设计相同的可重复使用运载火箭的其他要求。研究包括轨迹模拟和上升优化。考虑到推进剂的要求和车辆的载荷，LFBB考虑将其返回发射场。 CAD生成了不同的助力器形状，以进行初步的空气动力学尺寸确定，尺寸确定和质量估算。本文包括大型固体火箭发动机的液体反激助力器配置的性能比较和量化的排气数据。列出了相关火箭发动机的性能，质量，可重复使用性和节流能力。

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  • 来源
  • 会议地点 Noordwijk(NL)
  • 作者

    Martin Sippel; Uta Atanassov; Jens Kauffmann; Josef Klevanski; Volker Schmid;

  • 作者单位

    Space Launcher Systems Analysis (SART), DLR, Cologne, Germany Tel +49-2203-601-4778, Fax. +49-2203-601-2444, Martin.Sippel@dlr.de;

    rnSpace Launcher Systems Analysis (SART), DLR, Cologne, Germany Tel +49-2203-601-4778, Fax. +49-2203-601-2444;

    rnSpace Launcher Systems Analysis (SART), DLR, Cologne, Germany Tel +49-2203-601-4778, Fax. +49-2203-601-2444;

    rnSpace Launcher Systems Analysis (SART), DLR, Cologne, Germany Tel +49-2203-601-4778, Fax. +49-2203-601-2444;

    rnSpace Launcher Systems Analysis (SART), DLR, Cologne, Germany Tel +49-2203-601-4778, Fax. +49-2203-601-2444;

  • 会议组织
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 空气动力学;
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