Propulsion
Bi-Liquid LOX/Ethanol for Precise, Reliable Thrust
Development Steps:
High-Level Rocket Structure: Thrust Range, Vehicle Mass (+-50%)
Conservative(High-Thrust) Thruster / Feed System Design + Review
Fluid System Assembly, Testing, Calibration. Instrumentation and Control Development. Flight Structure Design Integration
Static Fire Testing. Mass Optimization, Simulation Refinement.
Flight Vehicle Integration
System Modules
Fluid System (Engine "Feed System")
Thruster + Injector
Priorities: Stable, Conservative Perfomance and Efficient Manufacturing/Assembly
Injector: Unlike-Doublet Impinging, LOX-centered
Chamber: Ablative + Fuel Jetted Wall-Film. 6061 Aluminum Jacket.
Nozzle: Graphite Throat, 316L Stainless Steel Expansion
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