Injection system for hybrid rockets with segmented fuel block

Injection system for hybrid rockets with segmented fuel block

The liquid component (oxydator) is guided in ring-shaped pipes on the outer or inner wall of the combustion chamber, e.g. the pipes follow the course of the gap between two fuel segments. The pipes have a large number of bores, e.g. through the chamber wall. The oxydator is injected in a star-shape...

Ausführliche Beschreibung

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Bibliographische Detailangaben
1. Verfasser: STINNESBECK, THOMAS., 53547 HUEMMERICH, DE
Format: Patent
Sprache:eng ; ger
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:The liquid component (oxydator) is guided in ring-shaped pipes on the outer or inner wall of the combustion chamber, e.g. the pipes follow the course of the gap between two fuel segments. The pipes have a large number of bores, e.g. through the chamber wall. The oxydator is injected in a star-shape through the bores, into the gap between two fuel segments.