Merlin 1A Merlin (rocket engine family)
spacex merlin 1a
the initial version, merlin 1a, used inexpensive, expendable, ablatively cooled carbon-fiber-reinforced polymer composite nozzle, , produced 340 kn (77,000 lbf) of thrust. merlin 1a flew twice: first on march 24, 2006, when caught fire , failed due fuel leak shortly after launch, , second time on march 21, 2007, when performed successfully. both times merlin 1a mounted on falcon 1 first stage.
the spacex turbopump entirely new, clean sheet design contracted barber-nichols, inc. in 2002 performed design, engineering analysis, , construction; company had worked on turbopumps rs-88 (bantam) , nasa fastrac engine programs. merlin 1a turbopump used unique friction-welded main shaft, inconel 718 ends , integral aluminum rp-1 impeller in middle. turbopump housing constructed using investment castings, inconel @ turbine end, aluminum in center, , 300-series stainless steel @ lox end. turbine partial-admission impulse design , turned @ 20,000 rpm, total weight of 150 lb.
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