Investigation of Dual-Thrust Rocket Motor with Subsonic Intermediate Nozzle

机译：亚音速中喷双推力火箭发动机的研究

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The Dual-Thrust Rocket Motors (DTRMs) are widely used solid propulsion system for various applications. These motors yield a variety of thrust-time profiles if the propellant characteristics and grain geometry are properly selected. DTRMs can have various designs; the DTRM with an intermediate nozzle is one design that yields a high boost-sustain thrust ratio with a stable operation. Depending on the internal conditions, the flow through the intermediate nozzle can be sonic, subsonic or reversed. The objective of this paper is to understand the internal ballistics (IB) phenomena of DTRM with subsonic intermediate nozzle. In this study, a mathematical model describing the performance of this DTRM is derived from the main governing equations of internal ballistics. Also, a set of experiments is conducted using a developed test motor to explore the physics of DTRM with subsonic intermediate nozzle and assess the mathematical model validity. Results of the theoretical and experimental investigation explain most of the IB characteristics that were not discussed before in the open literature.

机译：双推力火箭发动机（DTRM）是广泛用于各种应用的固体推进系统。如果正确选择了推进剂特性和颗粒几何形状，这些电动机将产生各种推力时间曲线。 DTRM可以具有多种设计;带有中间喷嘴的DTRM是一种设计，可产生高升压-持续推力比，并且运行稳定。根据内部条件，通过中间喷嘴的流量可以是声波，亚声波或反向。本文的目的是了解带有亚音速中间喷嘴的DTRM的内部弹道（IB）现象。在这项研究中，从内部弹道的主要控制方程中得出了描述此DTRM性能的数学模型。此外，使用开发的测试马达进行了一组实验，以探索亚音速中间喷嘴与DTRM的物理原理，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IB特性。

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《AIAA/SAE/ASEE joint propulsion conference;AIAA propulsion and energy forum》|2015年|5632-5643|共12页
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Amr M. El-Nady; Ahmed M. Sarhan; Mohamed A. Al-Sanabawy; Mahmoud Y. Mohamed;
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Internal Ballistics; Solid Propulsion; Dual Thrust Rocket Motor; Test Rocket Motor;

机译：内部弹道;固体推进;双推力火箭发动机;测试火箭发动机;

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1. Experimental and theoretical study on a dual-thrust rocket motor with subsonic intermediate nozzle [J] . El-Nady A. M., Ahmed M. Y. M., El-Senbawy M. A., Proceedings of the Institution of Mechanical Engineers . 2018,第10期

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
2. Experimental investigation of dual-thrust rocket motor with intermediate nozzle [J] . El-Nady Amr M., Ahmed Mahmoud Y.M., El-Senbawy Mohamed A., Journal of propulsion and power . 2017,第5期

机译：带有中间喷嘴的双推力火箭发动机的实验研究
3. Theoretical Analysis of Dual-Thrust Rocket Motors with Intermediate Nozzle [J] . A.M.El-Nady, A.M.Sarhan, M.A.El-Senbawy, Journal of propulsion and power . 2017,第2期

机译：中喷嘴双推力火箭发动机的理论分析
4. Investigation of Dual-Thrust Rocket Motor with Subsonic Intermediate Nozzle [C] . Amr M. El-Nady, Ahmed M. Sarhan, Mohamed A. Al-Sanabawy, AIAA/SAE/ASEE joint propulsion conference . 2015

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5. An investigation of the interaction between a travelling shock wave and a solid rocket motor nozzle. [D] . Chopra, Harmanjit Singh. 2003

机译：对行进的冲击波和固体火箭发动机喷嘴之间相互作用的研究。
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7. Dual-Thrust Rocket Motor with an intermediate Nozzle at the condition of higher boosting pressure than the sustaining pressure [O] . Amr El-Nady, Ahmed Sarhan, Mohamed Al-Sanabawy, 2015

机译：双推动火箭电机，中间喷嘴处于升高压力较高的条件，而不是维持压力
8. NASA Lewis Thermal Barrier Feasibility Investigated for Use in Space Shuttle Solid-Rocket Motor Nozzle-to-Case Joints [R] . Steinetz, Bruce M., Dunlap, Patrick H., Jr. 1999

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Investigation of Dual-Thrust Rocket Motor with Subsonic Intermediate Nozzle

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