A computer system, for manufacturing a solid rocket motor nozzle using additive manufacturing, inputs into a temperature field algorithm at least one design parameter for the solid rocket motor nozzle. The temperature field algorithm generates a first temperature field for an initial solid rocket motor nozzle design. The first temperature field is provided to a nozzle-geometry optimization algorithm. The nozzle-geometry optimization algorithm generates a first updated solid rocket motor nozzle design. The temperature field algorithm then generates a second temperature field for the first updated solid rocket motor nozzle design. The second temperature field is provided to the nozzle-geometry optimization algorithm. The nozzle-geometry optimization algorithm generates a second updated solid rocket motor nozzle design. When the second updated solid rocket motor nozzle design meets a specified project requirement, the computer system generates a file for additively manufacturing the second updated solid rocket motor nozzle design.


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    Titel :

    ADDITIVELY MANUFACTURED, THERMALLY OPTIMIZED ROCKET MOTOR NOZZLE DESIGN


    Beteiligte:

    Erscheinungsdatum :

    25.04.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / F02K JET-PROPULSION PLANTS , Strahltriebwerke