AbstractA design methodology is presented that supports the design of future aerospace rocket-powered vehicles. In particular, it provides the capabilities to rapidly evaluate the performance, weight, size, and lifecycle costs of all chemical rocket engines at a conceptual level. By leveraging cycle-based approaches and surrogate modeling techniques, the performance of all chemical rocket engines can be evaluated with an accuracy of 3%, whereas it divides the execution time by a factor of 105 compared to current physics-based models. New mass-estimating relationships are developed for estimating the weight and the size of solid engines with an improved accuracy compared to existing models. Physics-based models built around the key design drivers are used for the weight and size estimation of liquid and hybrid engines. Although existing cost-estimating relationships are used to evaluate the lifecycle costs of solid and liquid engines, a more physics-based model is developed for hybrid engines. Although it supports complex multiobjective optimizations and rapid trade-off analyses, this environment is also the first of its sort able to estimate the lifecycle costs of hybrid rocket engines.


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    Title :

    Design Methodology for the Performance, Weight, and Economic Assessment of Chemical Rocket Engines




    Publication date :

    2016




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 51.40 Werkstoffe für bestimmte Anwendungsgebiete / 55.60 Raumfahrttechnik
    Local classification TIB:    770/7040



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