High regression rate hybrid rocket propellants
    2.
    发明授权
    High regression rate hybrid rocket propellants 失效
    高回归率混合火箭推进剂

    公开(公告)号:US06684624B2

    公开(公告)日:2004-02-03

    申请号:US09359149

    申请日:1999-07-21

    IPC分类号: C06B4510

    CPC分类号: C06D5/00 C06B47/02 F02K9/72

    摘要: This invention comprises a new process for developing high regression rate propellants for application to hybrid rockets and solid fuel ramjets. The process involves the use of a criterion to identify propellants which form an unstable liquid layer on the melting surface of the propellant. Entrainment of droplets from the unstable liquid-gas interface can substantially increase propellant mass transfer leading to much higher surface regression rates over those that can be achieved with conventional hybrid propellants. The main reason is that entrainment is not limited by heat transfer to the propellant from the combustion zone. The process has been used to identify a new class of non-cryogenic hybrid fuels whose regression rate characteristics can be tailored for a given mission. The fuel can be used as the basis for a simpler hybrid rocket design with reduced cost, reduced complexity and increased performance.

    摘要翻译: 本发明包括用于开发用于混合火箭和固体燃料雷击的高回归率推进剂的新方法。 该方法涉及使用标准来鉴定在推进剂的熔融表面上形成不稳定液体层的推进剂。 来自不稳定液 - 气界面的液滴的夹带可以显着增加推进剂传质,导致比常规混合推进剂可以实现的更高的表面回归率。 主要原因是夹带不受限于从燃烧区向推进剂的传热。 该过程已被用于确定一类新一代的非低温混合燃料,其回归率特征可以针对特定任务进行调整。 燃料可以用作更简单的混合火箭设计的基础,降低成本,降低复杂性并提高性能。

    High regression rate hybrid rocket propellants and method of selecting
    8.
    发明授权
    High regression rate hybrid rocket propellants and method of selecting 失效
    高回归率混合火箭推进剂和选择方法

    公开(公告)号:US06880326B2

    公开(公告)日:2005-04-19

    申请号:US09505516

    申请日:2000-02-17

    CPC分类号: C06D5/00 C06B47/02 F02K9/72

    摘要: This invention comprises a new process for developing high regression rate propellants for application to hybrid rockets and solid fuel ramjets. The process involves the use of a criterion to identify propellants which form an unstable liquid layer on the melting surface of the propellant. Entrainment of droplets from the unstable liquid-gas interface can substantially increase propellant mass transfer leading to much higher surface regression rates over those that can be achieved with conventional hybrid propellants. The main reason is that entrainment is not limited by heat transfer to the propellant from the combustion zone. The process has been used to identify a new class of non-cryogenic hybrid fuels whose regression rate characteristics can be tailored for a given mission. The fuel can be used as the basis for a simpler hybrid rocket design with reduced cost, reduced complexity and increased performance.

    摘要翻译: 本发明包括用于开发用于混合火箭和固体燃料雷击的高回归率推进剂的新方法。 该方法涉及使用标准来鉴定在推进剂的熔融表面上形成不稳定液体层的推进剂。 来自不稳定液 - 气界面的液滴的夹带可以显着增加推进剂传质,导致比常规混合推进剂可以实现的更高的表面回归率。 主要原因是夹带不受限于从燃烧区向推进剂的传热。 该过程已被用于确定一类新一代的非低温混合燃料,其回归率特征可以针对特定任务进行调整。 燃料可以用作更简单的混合火箭设计的基础,降低成本,降低复杂性并提高性能。