In this study, the conceptual design of a single-stage hybrid rocket engine of a low-altitude sounding rocket is developed using the Multi-Objective Vibrational Genetic Algorithm (MOVGA). A hybrid rocket engine design having single circular port fuel grain with constant cross-section doped with oxidizer is done. Hybrid rocket engine is fueled by Hydroxyl-Terminated Polybutadiene (HTPB) with oxygen as the oxidizer. This is probably the first study in which the MOVGA is used for a hybrid rocket engine design problem. Vibrational genetic algorithm used in the hybrid rocket engine design problem as a comprehensive mutation technique provides diversity in the population in order to explore and find the global optimum quickly. For a high efficient hybrid rocket, the design problem is formulated as maximization of the flight altitude with minimum total mass with engine size (length to diameter ratio) constraint. The algorithm estimates the optimum hybrid rocket engine design including thrust, sizing and flight altitude calculations. Consequently, a mechanical design of a manufacturable and testable hybrid rocket engine is accomplished by means of the MOVGA in reasonable CPU times.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Hybrid rocket engine design with multi-objective vibrational genetic algorithm


    Contributors:


    Publication date :

    2017-06-01


    Size :

    387782 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English





    HYBRID ROCKET ENGINE TEST FACILITY DESIGN

    Ali Emre Samur / Abdurrahman Hacıoğlu / Arif Karabeyoğlu | DOAJ | 2016

    Free access

    Feasibility Study of Multi Objective Shape Optimization for Rocket Engine Turbopump Blade Design

    Tani, Naoki / Oyama, Akira / Yamanishi, Nobuhiro et al. | AIAA | 2008