The exploratory development effort included the design, fabrication, and testing of injectors, ablative thrust chambers, and a radiation-cooled-divergent nozzle extension.
Development and Demonstration of Ablative Thrust Chamber Assemblies Using LF2/N2H4 Blend Propellants
1969
374 pages
Report
No indication
English
Rocket Engines & Motors , Rocket Propellants , Combustion & Ignition , Liquid propellant rocket engines , Fuel injectors , Combustion chambers , Liquid rocket propellants , Combustion , Stability , Combustion chamber liners , Hydrazine , Altitude , Fluorine , Simulation , Propellant control , Liquefied gases , Ablation , Captive tests , Fuel injection , Performance(Engineering) , Thermal analysis , Rocket nozzles , Heat resistant materials , Nozzle inserts , Thermal radiation , Convergent divergent nozzles , Nozzle throats , Compatibility , Structural properties , Composite materials , Ablative materials , Acoustic resonators , Carbon fibers , Graphite
Ablative Thrust Chamber Feasibility
NTIS | 1963
Development and Demonstration of a N2O4/N2H4 Injector
NTIS | 1969
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