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Nozzle Optimization of Dual Thrust Rocket Motors

descriptionPublicationkeyboard_double_arrow_right Part of book or chapter of book , Other literature type , Conference object 24 Apr 2019 Serbia English Publisher:Springer International PublishingFunded by:MESTD | Cost-effective selection ...

Authors: Alazeezi, Mohammed; Elek, Predrag;

doi: 10.1007/978-3-030-18072-0_54

handle: 21.15107/rcub_machinery_4911

Nozzle Optimization of Dual Thrust Rocket Motors

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Abstract

Optimizing the nozzle of a solid propellant rocket motor plays an essential rule in the overall performance of the motor. In this paper, the investigation of an optimization model of dual thrust propellant rocket motors will be presented. Due to having two phases of thrust in this type of rocket motors, determination of the rocket nozzle expansion ratio is a non-trivial problem. The idea is to use a simple, fixed length and expansion ratio, convergent-divergent nozzle, which provides the highest total impulse of the motor. Usual assumptions for an ideal rocket motor have been used. The optimization model was developed in MATLAB and calculations has been performed using previously obtained interior ballistic and other relevant data for a dual thrust solid propellant rocket motor.

Country

Serbia

Related Organizations

University of Belgrade, Faculty of Mechanical Engineering
Serbia
University of Belgrade
Serbia

Keywords

Optimization, dual thrust, Rocket propulsion, convergent-divergent nozzle, Convergent-divergent nozzle, optimization, rocket propulsion, Dual thrust

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