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High regression rate hybrid rocket propellants and method of selecting

机译:高回归率混合火箭推进剂及其选择方法

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.
机译:本发明包括开发用于混合火箭和固体燃料冲压喷气发动机的高回归速率推进剂的新方法。该方法涉及使用标准来识别在推进剂的熔融表面上形成不稳定液体层的推进剂。从不稳定的液-气界面夹带的液滴会大大增加推进剂的传质,从而导致比传统的混合推进剂所能达到的更高的表面退化率。主要原因是夹带不受从燃烧区传给推进剂的热量的限制。该过程已被用于识别一类新型的非低温混合燃料,其回归速率特性可以针对特定任务进行定制。燃料可以用作更简单的混合火箭设计的基础,从而降低成本,降低复杂性并提高性能。

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