Browsing by Author "El-Senbawy, M. A."

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    Experimental and theoretical study on a dual-thrust rocket motor with subsonic intermediate nozzle
    (SAGE PUBLICATIONS LTD, 2018) El-Nady, A. M.; Ahmed, M. Y. M.; El-Senbawy, M. A.
    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.
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    Experimental Investigation of Dual-Thrust Rocket Motor with Intermediate Nozzle
    (AMER INST AERONAUTICS ASTRONAUTICS, 2017) El-Nady, A. M; Ahmed, M. Y. M; El-Senbawy, M. A.; Sarhan, A. M.
    Dual-thrust solid propellant rocket motors are used in applications where the vehicle is boosted with a high thrust to reach very quickly a high speed that is then sustained by a low thrust. Dual-thrust rocket motors have a variety of designs; however, the one with intermediate nozzle yields high thrust ratio as well as a stable operation. Motivated by the shortage in related studies, the present paper is intended to shed more light on the topic of dual-thrust rocket motors with intermediate nozzle. The paper discusses the results of a set of static firing tests on a developed test motor covering all modes of motor operation. It is found that the thrust ratio can be maximized if the pressure difference across the intermediate nozzle is minimized. If the flow through the intermediate nozzle is initially reversed, a risk of motor damage should be taken into account.