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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Experimental and theoretical study on a dual-thrust rocket motor with subsonic intermediate nozzle
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Experimental and theoretical study on a dual-thrust rocket motor with subsonic intermediate nozzle

机译：亚音速中间喷嘴双推力火箭发动机的实验和理论研究

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摘要

Dual-thrust rocket motors, with proper designs, can yield the desired boost-sustain thrust profiles for a variety of applications. Of the various designs that a dual-thrust rocket motor can have, the one with an intermediate nozzle provides a high boost-to-sustain thrust ratio as well as a stable operation. Depending on the internal conditions, the flow through the intermediate nozzle in the boost phase can be sonic, subsonic, or initially reversed. The present paper discusses the operation and performance of Dual-thrust rocket motors with subsonic intermediate nozzle. A mathematical model describing the internal ballistics of these dual-thrust rocket motors is derived from the basic governing equation. In addition, a set of experiments is conducted using a developed test motor to explore the physics of dual-thrust rocket motors with subsonic intermediate nozzle and assess the mathematical model validity. Results of the theoretical and experimental investigations explain most of the internal ballistics characteristics that were not discussed before in the open literature.
机译：具有适当设计的双推力火箭发动机可以为各种应用提供所需的助推-持续推力曲线。在双推力火箭发动机可以具有的各种设计中，带有中间喷嘴的设计可提供高的推力-维持推力比以及稳定的运行。根据内部条件，在增压阶段通过中间喷嘴的流量可以是声波，亚声波或最初反向的。本文讨论了具有亚音速中间喷嘴的双推力火箭发动机的运行和性能。从基本控制方程中得出了描述这些双推力火箭发动机内部弹道的数学模型。此外，使用开发的测试电动机进行了一组实验，以探索具有亚音速中间喷嘴的双推力火箭发动机的物理特性，并评估了数学模型的有效性。理论和实验研究的结果解释了公开文献之前未讨论过的大多数内部弹道特征。

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