ROCKET ENGINE WITH DUAL CONTOUR NOZZLE

ROCKET ENGINE WITH DUAL CONTOUR NOZZLE

A rocket engine includes a primary chamber and a double contour nozzle attached to the primary chamber. The double contour nozzle includes an inner contour nozzle, an outer contour nozzle, and a transition region between the inner contour nozzle. The inner contour nozzle includes a conical contour....

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Muss, Jeffery Alan, Malik, Asad
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung:A rocket engine includes a primary chamber and a double contour nozzle attached to the primary chamber. The double contour nozzle includes an inner contour nozzle, an outer contour nozzle, and a transition region between the inner contour nozzle. The inner contour nozzle includes a conical contour. The outer contour nozzle includes a bell contour and at least one propellant injection orifice. The contour break point includes a radius of curvature that is less than 0.75 and a tangency angle that is in a range of from 40 degrees to 90 degrees.