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.
ADDITIVELY MANUFACTURED, THERMALLY OPTIMIZED ROCKET MOTOR NOZZLE DESIGN
2024-04-25
Patent
Electronic Resource
English
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 |