• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Conceptual study of a dual-rocket-based- combined-cycle powered two-stage-to- orbit launch vehicle
【24h】

Conceptual study of a dual-rocket-based- combined-cycle powered two-stage-to- orbit launch vehicle

机译：基于双火箭的联合循环动力两阶段轨道运载火箭的概念研究

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The liquid oxygen/methane staged cycle liquid-rocket engine is one of the most potential rocket engines in the future for its higher performance, higher fuel density and reusable capacity. Two working states of this liquid-rocket engine named as full-load state and half-load state are defined in this paper. Based on this liquid-rocket engine, a dual-rocket-based-combined-cycle propulsion system with liquid oxygen /air/methane as propellants is therefore proposed. The dual-rocket-based-combined-cycle system has then five working modes: the hybrid mode, pure ejector mode, ramjet mode, scramjet mode and pure rocket mode. In hybrid mode, the booster and ejector rockets driven by the full-load liquid-rocket engine work together with the purpose of reducing thrust demand on ejector rocket. In scramjet mode, the fuel-rich burned hot gas generated by the half-load liquid-rocket engine is used as fuel, which is helpful to reduce the technical difficulty of scramjet in hypersonic speed. The five working modes of dual-rocket-based-combined-cycle are highly integrated based on the full- or half-load state of the liquid oxygen/methane staged cycle liquid-rocket engine, and the unified single type fuel of liquid methane is adopted for the whole modes. Then a preliminary design of a horizontal takeoff two-stage-to-orbit launch vehicle is conducted based on the dual-rocket-based-combined-cycle propulsion system. Under an averaged baseline thrust and specific impulse, the launch trajectory to reach a low Earth orbit at 100km is optimized via the pseudo-spectral method subject to maximizing the payload mass. It is shown that the two-stage-to-orbit vehicle based on the dual-rocket-based-combined-cycle can achieve the payload mass fraction of 0.0469 and 0.0576 for polar mission and equatorial mission, respectively. Conclusively, insights gained in this paper can be usefully applied to a more detailed design of the dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle.
机译：液氧/甲烷分级循环液体火箭发动机以其更高的性能，更高的燃料密度和可重复使用的容量而成为未来最有潜力的火箭发动机之一。本文定义了该液体火箭发动机的两个工作状态，分别为满载状态和半载状态。因此，基于这种液体火箭发动机，提出了一种以液体氧/空气/甲烷为推进剂的基于双火箭的联合循环推进系统。基于双火箭的联合循环系统具有五个工作模式：混合模式，纯喷射器模式，冲压喷射模式，超燃冲压喷射模式和纯火箭弹模式。在混合模式下，由满载液体火箭发动机驱动的助推器和推顶火箭共同工作，目的是减少推顶火箭的推力需求。在超燃冲压发动机模式下，将半负荷液体火箭发动机产生的富含燃料的燃烧热气用作燃料，这有助于降低超燃速超燃发动机的技术难度。基于液氧/甲烷分级循环液体火箭发动机的全负荷或半负荷状态，高度集成了双火箭联合循环的五种工作模式，而液态甲烷的统一单一燃料为整个模式都采用。然后，基于双火箭联合循环推进系统，对水平起飞两阶段入轨运载火箭进行了初步设计。在平均基线推力和比冲的情况下，通过伪谱法优化了到达100公里低地球轨道的发射轨迹，以使有效载荷质量最大化。结果表明，基于双火箭组合循环的两阶段入轨飞行器在极地飞行和赤道飞行中的有效载荷质量分数分别为0.0469和0.0576。结论是，本文中获得的见解可有效地应用于基于双火箭的联合循环动力两级入轨运载火箭的更详细设计。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号