| 词条 | Fastrac (rocket engine) |
| 释义 |
|name=Fastrac MC-1 |country_of_origin=United States |manufacturer=NASA |purpose=small, cheap, expendable rockets |type=liquid |fuel=RP-1 (rocket grade kerosene) |oxidiser=LOX |capacity= |thrust(Vac)= {{convert|60000|lbf|kN|abbr=on}} |specific_impulse_vacuum= 314 s (3.0 km/s)[1] |specific_impulse_sea_level= |chamber_pressure= |thrust_to_weight= |cycle=gas-generator |diameter={{convert|1.22|m|abbr=on}}[2] |length={{convert|2.13|m|abbr=on}}[2] |dry_weight=less than {{convert|910|kg|abbr=on}}[3] }} Fastrac or alternatively MC-1 engine was a pump-fed liquid rocket engine developed by NASA for use on small inexpensive, expendable rockets. Fastrac uses RP-1 kerosene and liquid oxygen as propellants in a gas-generator power cycle. Ignition of engine was achieved via starter fluid injected into combustion chamber before kerosene was fed. Propellants are fed via a single shaft, dual impeller turbo-pump. The engine design used an inexpensive, expendable, ablatively cooled carbon fiber composite nozzle, and produced 60,000 lbf (285 kN) of thrust. Engine system development testing of the MC-1 began in 1997 [4] and continued until the Fastrac program was cancelled 2001,[5] 48 tests were conducted on three engines using three separate test stands.[6] The engine never flew, but with NASA's cooperation much of the MC-1 design and technology was adopted by the private corporation SpaceX for its Merlin 1A engine[7] MC-1 later designationAfter the cancellation of the FASTRAC program{{when|date=January 2013}} NASA tried to salvage this design for use in other rockets such as Rotary Rocket's Roton and Orbital's X-34 project. The designation of the rocket engine was changed from the Fastrac 60K to MC-1. LegacyThe basic principles of the Fastrac design (namely, a pintle injector and ablatively cooled chamber) lived on in SpaceX's Merlin 1A engine, which used a turbopump from the same subcontractor.[7] The Merlin-1A was somewhat larger engine with a thrust of {{convert|77000|lbf|kN|abbr=on}} versus {{convert|60000|lbf|kN|abbr=on}} for Fastrac. The same basic design was capable of much higher thrust levels after upgrading the turbopump. The latest variants of the Merlin-1D achieve {{convert|185500|lbf|kN|abbr=on}} of thrust as of April 2016, but is a regeneratively cooled engine.[8] Engine specifications
See also
References{{Include-NASA}}1. ^{{citation|title=Systems Analysis of a High Thrust Low-Cost Rocket Engine|url=http://www.la.dlr.de/ra/sart/publications/pdf/esa02-2001.pdf|format=PDF}} 2. ^1 astronautix 3. ^NASA Solutions - Fastrac 4. ^https://ntrs.nasa.gov/search.jsp?R=20000064017 5. ^{{citation|title=40K Fastrac II Bantam Test|url=https://mix.msfc.nasa.gov/abstracts.php?p=2955}} 6. ^{{citation|title=Development Status of the NASA MC-1 (Fastrac) Engine|url=https://ntrs.nasa.gov/search.jsp?R=20000097369|format=PDF}} 7. ^1 Barber-Nichols, Inc turbopumps 8. ^{{citation|title=SpaceX CASSIOPE Mission Press Kit (Sept 2013) pg. 10|url=http://www.spacex.com/sites/spacex/files/spacex_upgradedf9demomission_presskit.pdf|format=PDF}} 9. ^{{Cite web|url=https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000112951.pdf|title=A Regeneratively-Cooled Thrust Chamber for the FASTRAC Engine|last=|first=|date=|website=|archive-url=|archive-date=|dead-url=|access-date=}}
External links
3 : Rocket engines using kerosene propellant|Rocket engines using the gas-generator cycle|Rocket engines of the United States |
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