Experimental and theoretical study on a dual-thrust rocket motor with subsonic intermediate nozzle

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Date

2018

Journal Title

Journal ISSN

Volume Title

Type

Article

Publisher

SAGE PUBLICATIONS LTD

Series Info

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING;Volume: 232 Issue: 10 Pages: 1844-1852

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Abstract

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.

Description

Accession Number: WOS:000439608000004

Keywords

University for Solid propellant rocket propulsion, dual-thrust rocket motor, thrust ratio, intermediate nozzle, static firing tests

Citation

Cited References in Web of Science Core Collection: 9