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→MC-1 later designation: Rotary Rocket was the company, Roton was the vehicle. More Wikification. Grammar
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{{short description|Pump-fed liquid rocket engine developed by NASA for use on small inexpensive, expendable rockets}} |
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{{About|the rocket engine||Fastrac (disambiguation){{!}}Fastrac}} |
{{About|the rocket engine||Fastrac (disambiguation){{!}}Fastrac}} |
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{{infobox rocket engine |
{{infobox rocket engine |
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|name=Fastrac MC-1 |
|name=Fastrac MC-1 |
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|image=File:X-34 40K Fastrac II Engine Test (9705975).jpg |
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|caption=Fastrac engine during test at Marshall Space Flight Center test stand 116 |
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|country_of_origin=[[United States]] |
|country_of_origin=[[United States]] |
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|manufacturer=[[NASA]] |
|manufacturer=[[NASA]] |
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|purpose= |
|purpose=Low Cost Booster Technology, X-34 |
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|type=liquid |
|type=liquid |
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| Line 11: | Line 14: | ||
|capacity= |
|capacity= |
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|thrust(Vac)= {{convert|60000|lbf|kN|abbr=on}}<ref>{{cite web | url=https://www.barber-nichols.com/sites/default/files/wysiwyg/images/rocket_engine_turbopumps.pdf | accessdate=September 7, 2019|title=Rocket Engine Turbopumps|publisher=Barber Nicols}}</ref> |
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|thrust(Vac)= {{convert|60000|lbf|kN|abbr=on}} |
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|specific_impulse_vacuum= 314 s (3.0 km/s)<ref name="ESA">{{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| |
|specific_impulse_vacuum= 314 s (3.0 km/s)<ref name="ESA">{{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|access-date=2012-03-31|archive-url=https://web.archive.org/web/20160304030932/http://www.la.dlr.de/ra/sart/publications/pdf/esa02-2001.pdf|archive-date=2016-03-04|url-status=dead}}</ref> |
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|specific_impulse_sea_level= |
|specific_impulse_sea_level= |
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|chamber_pressure= |
|chamber_pressure= |
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|cycle=[[Gas-generator cycle (rocket)|gas-generator]] |
|cycle=[[Gas-generator cycle (rocket)|gas-generator]] |
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|diameter={{convert|1.22|m|abbr=on}}<ref name="astro"> |
|diameter={{convert|1.22|m|abbr=on}}<ref name="astro">{{cite web|url=http://www.astronautix.com/engines/fastrac.htm|title=Fastrac|website=www.astronautix.com|archive-url=https://web.archive.org/web/20160303193747/http://www.astronautix.com/engines/fastrac.htm|archive-date=3 March 2016|url-status=dead}}{{cbignore|bot=medic}}</ref> |
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|length={{convert|2.13|m|abbr=on}}<ref name="astro" /> |
|length={{convert|2.13|m|abbr=on}}<ref name="astro" /> |
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|dry_weight=less than {{convert|910|kg|abbr=on}} |
|dry_weight=less than {{convert|910|kg|abbr=on}} |
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}} |
}} |
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'''Fastrac''' was a turbo [[Pump-fed engine|pump-fed]], liquid [[rocket engine]]. The engine was designed by [[NASA]] as part of the low cost [[Orbital Sciences X-34|X-34]] Reusable Launch Vehicle (RLV)<ref name="MSFC"/> and as part of the Low Cost Booster Technology (LCBT, aka Bantam) project.<ref>{{cite web | url=https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20010020058.pdf | accessdate=September 6, 2019 | title=Fabrication of Composite Combustion Chamber/Nozzle For Fastrac Engine| date=January 2000 }}</ref> This engine was later known as the MC-1 engine when it was merged into the [[X-34]] project. |
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'''Fastrac''' or alternatively '''MC-1 engine''' was a [[Pump-fed engine|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 cycle (rocket)|gas-generator]] power cycle. |
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==Design== |
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Ignition of engine was achieved via starter fluid injected into combustion chamber before kerosene was fed. |
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The turbopump engine was designed to be used in an expendable booster in the LCBT project. As a result this led to the use of composite materials because of their significantly lower costs and production speed; this also reduced engine complexity since the fuel was not used for nozzle cooling. Based on knowledge and experience from the [[Space Shuttle]]'s Reusable Solid Rocket Motor (RSRM) and the Solid Propulsion Integrity Program (SPIP),<ref>{{cite web | url=https://archive.org/details/nasa_techdoc_19930012915 | accessdate=September 6, 2019 | title=Solid Propulsion Integrity Program for Verifiable Enhanced Solid Rocket Motor Reliablility| date=February 1993 }}</ref> a [[Silica]]/phenolic material was chosen for the [[Ablation|ablative]] liner with carbon/epoxy structural overlap. |
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The engine fuel was a mixture of [[liquid oxygen]] and [[kerosene]] ([[RP-1]]). These propellants are used by [[Rocketdyne F-1|Saturn F1]] rocket engine. Kerosene does not have the same energy release as hydrogen, used with the [[Space Shuttle]], but it is cheaper and easier to handle and store. Propellants were fed via a single shaft, dual impeller LOX/RP-1 [[turbo-pump]].<ref name="Rocket Engine Turbopumps">{{cite web|url=https://www.barber-nichols.com/products/rocket-engine-turbopumps|accessdate=September 6, 2019|title=Rocket Engine Turbopumps}}</ref> |
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Propellants are fed via a single shaft, dual impeller [[turbo-pump]]. |
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The engine was started with a [[Hypergolic propellant|hypergolic igniter]] to maintain a simple design. Kerosene was injected and the engine was then running. The propellants were then fed into the gas generator for mixing and thrust chamber for burning. |
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| ⚫ |
The engine |
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The engine uses a [[gas generator]] cycle to drive the turbo-pump turbine, which then exhausts this small amount of spent fuel. This is the identical cycle used with the Saturn rockets, but much less complex than the Space Shuttle engine system. |
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Engine system development testing of the MC-1 began in 1997 <ref>https://ntrs.nasa.gov/search.jsp?R=20000064017</ref> and continued until the Fastrac program was cancelled 2001,<ref name="MSFC">{{citation|title=40K Fastrac II Bantam Test|url=https://mix.msfc.nasa.gov/abstracts.php?p=2955}}</ref> 48 tests were conducted on three engines using three separate test stands.<ref name="DevelStatus">{{citation|title=Development Status of the NASA MC-1 (Fastrac) Engine|url=https://ntrs.nasa.gov/search.jsp?R=20000097369|format=PDF}}</ref> |
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| ⚫ | The engine used an inexpensive, expendable, [[Ablation|ablatively cooled]] [[carbon fiber]] [[Composite material|composite]] nozzle and produced 60,000 lbf (285 kN) of thrust. After use nearly all of the engine's parts are reusable.<ref>{{cite web | url=https://www.nasa.gov/centers/marshall/news/background/facts/fastrac.html|title=Fastrac Engine -- A Boost for Low-cost Space Launch}}</ref> |
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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 (rocket engine)|Merlin 1A engine]]<ref name="Barber-Nichols, Inc turbopumps">[http://www.barber-nichols.com/products/rocket-engine-turbopumps/ Barber-Nichols, Inc turbopumps]</ref> |
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During the research phase in 1999 each Fastrac engine was costed at approximately $1.2 million.<ref>{{cite web | url=http://www.astronautix.com/f/fastrac.html | accessdate=September 6, 2019 | title= Fastrac}}</ref> Production costs were expected to drop to $350,000 per engine. |
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==MC-1 later designation== |
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== History == |
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After 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 Sciences|Orbital]]'s [[X-34]] project. |
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Engine system level testing started in 1999 at the [[Stennis Space Center]].<ref>{{Cite web|url=https://ntrs.nasa.gov/search.jsp?R=20000064017|title=NASA Technical Reports Server (NTRS) - NASA Fastrac Engine Gas Generator Component Test Program and Results|date=January 2000 }}</ref> Earlier tests were on individual components at the [[Marshall Space Flight Center]]. NASA started full-engine, hot-fire testing in March, 1999, with a 20 second test to demonstrate the complete engine system.<ref>{{cite web | url=https://www.sciencedaily.com/releases/1999/03/990315135743.htm | accessdate=6 September 2019 |title=Fastrac Full-Engine, Hot-Fire Test Successful }}</ref> The engine was tested at full power for 155 seconds on July 1, 1999.<ref>{{cite web|url=http://www.spacedaily.com/news/rlv-99l.html|accessdate=September 7, 2019|title=X-34 Fastrac Engine Tested}}</ref> A total of 85 tests were scheduled for the rest of 1999. As of 2000, 48 tests had been conducted on three engines using three test stands.<ref name="DevelStatus">{{citation|title=Development Status of the NASA MC-1 (Fastrac) Engine| date=January 2000 |url=https://ntrs.nasa.gov/search.jsp?R=20000097369|format=PDF}}</ref> |
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The designation of the rocket engine was changed from the Fastrac 60K to MC-1. |
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The first engine was installed on the X-34 A1 vehicle that was unveiled at NASA's Dryden Flight Research Center on April 30, 1999.<ref name="Rocket Engine Turbopumps"/> |
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The Fastrac program was cancelled in 2001.<ref name="MSFC">{{citation|title=40K Fastrac II Bantam Test|url=https://mix.msfc.nasa.gov/abstracts.php?p=2955|access-date=2015-01-11|archive-url=https://web.archive.org/web/20150721071625/https://mix.msfc.nasa.gov/abstracts.php?p=2955|archive-date=2015-07-21|url-status=dead}}</ref> After FASTRAC, NASA tried to salvage this design for use in other rockets such as [[Rotary Rocket]]'s Roton and [[Orbital Sciences|Orbital]]'s [[X-34]] project. The designation of the rocket engine was changed from the Fastrac 60K to Marshall Center - 1 (MC-1). The MC-1 project was closed by July, 2009, after the [[X-34]] project was terminated in March, 2009.<ref>{{cite web|url=https://sscwebpub.ssc.nasa.gov/etd/ETDPropulsionSS_MC1.asp|accessdate=September 7, 2019|title=Marshall Center-1 (MC-1) Test Program|archive-date=August 13, 2020|archive-url=https://web.archive.org/web/20200813232235/https://sscwebpub.ssc.nasa.gov/etd/ETDPropulsionSS_MC1.asp|url-status=dead}}</ref> |
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==Components== |
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NASA collaborated with industry partners to meet the principal objective to use commercial, off-the-shelf components. Industry partners included Summa Technology Inc., [[AlliedSignal|Allied Signal]] Inc., [[Marotta|Marotta Scientific Controls]] Inc., Barber-Nichols Inc., and [[Thiokol|Thiokol Propulsion]]. |
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== Legacy == |
== Legacy == |
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A similar set of technical solutions that reduce the cost of the engine was implemented in the [[SpaceX|SpaceX's]] [[Merlin 1A]] engine, which used a turbopump from the same subcontractor.<ref name="Barber-Nichols, Inc turbopumps">{{Cite web|url=https://www.barber-nichols.com/products/rocket-engine-turbopumps/|title=Rocket Engine Turbopumps | Barber Nichols|website=www.barber-nichols.com}}</ref> The Merlin-1A was somewhat larger 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. Variants of the Merlin-1D achieve {{convert|190000|lbf|kN|abbr=on}} of thrust as of May, 2018,<ref>{{cite tweet |first=Eric |last=Berger |user=SciGuySpace |number=994649495861432321 |date=10 May 2018 |title=Musk: Merlin rocket engine thrust increased by 8 percent, to 190,000 lbf. }}</ref> though the combustion chamber is now [[Regenerative cooling (rocket)|regeneratively cooled]].<ref name="SPX_PK">{{citation|title=SpaceX CASSIOPE Mission Press Kit (Sept 2013) pg. 10|url=http://www.spacex.com/sites/spacex/files/spacex_upgradedf9demomission_presskit.pdf|access-date=2015-01-11|archive-date=2017-04-12|archive-url=https://web.archive.org/web/20170412000244/http://www.spacex.com/sites/spacex/files/spacex_upgradedf9demomission_presskit.pdf|url-status=dead}}</ref> |
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The basic principles of the Fastrac design (namely, a [[pintle injector]] and ablatively cooled chamber) lived on in [[SpaceX|SpaceX's]] [[Merlin (rocket engine)|Merlin 1A engine]], which used a turbopump from the same subcontractor.<ref name="Barber-Nichols, Inc turbopumps"/> |
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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 [[Regenerative cooling (rocket)|regeneratively cooled]] engine.<ref name="SPX_PK">{{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}}</ref> |
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==Specifications== |
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==Engine specifications== |
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*Vacuum thrust: |
*Vacuum thrust: {{convert|60000|lbf|kN|abbr=on}} |
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*Vacuum specific impulse: |
*Vacuum specific impulse: 314 s (3.0 kN·s/kg) |
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*Chamber pressure: 633 psi <ref>{{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=https://web.archive.org/web/20180724181218/https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20000112951.pdf|archive-date=2018-07-24|url-status=dead|access-date=}}</ref> |
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*Chamber pressure: |
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*Total mass flow: |
*Total mass flow: 91.90 kg/s |
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*Gas generator pressure: 39.64 bar |
*Gas generator pressure: 39.64 bar |
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*Gas generator temperature: 888.89 K |
*Gas generator temperature: 888.89 K |
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*Throat diameter: 0.22 m |
*Throat diameter: 0.22 m |
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*Fuel: |
*Fuel: RP-1 (rocket grade kerosene) |
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*Oxidizer: |
*Oxidizer: Liquid oxygen |
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== See also == |
== See also == |
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{{Include-NASA}} |
{{Include-NASA}} |
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{{reflist|2}} |
{{reflist|2}} |
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;Note |
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;Notes |
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{{refbegin}} |
{{refbegin}} |
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*{{cite web|url=http://www.nasa.gov/centers/marshall/news/background/facts/fastrac.html |title=NASA FASTRAC engine program |year=1999 }} |
*{{cite web|url=http://www.nasa.gov/centers/marshall/news/background/facts/fastrac.html |title=NASA FASTRAC engine program |year=1999 }} |
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==External links== |
==External links== |
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* [http://www.nasa.gov/centers/marshall/news/background/facts/fastrac.html NASA |
* [http://www.nasa.gov/centers/marshall/news/background/facts/fastrac.html NASA Fastrac Overview. 1999] |
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{{Rocket engines}} |
{{Rocket engines}} |
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Fastrac engine during test at Marshall Space Flight Center test stand 116
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| Country of origin | United States |
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| Manufacturer | NASA |
| Application | Low Cost Booster Technology, X-34 |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 (rocket grade kerosene) |
| Cycle | gas-generator |
| Performance | |
| Thrust, vacuum | 60,000 lbf (270 kN)[1] |
| Specific impulse, vacuum | 314 s (3.0 km/s)[2] |
| Dimensions | |
| Length | 2.13 m (7 ft 0 in)[3] |
| Diameter | 1.22 m (4 ft 0 in)[3] |
| Dry weight | less than 910 kg (2,010 lb) |
Fastrac was a turbo pump-fed, liquid rocket engine. The engine was designed by NASA as part of the low cost X-34 Reusable Launch Vehicle (RLV)[4] and as part of the Low Cost Booster Technology (LCBT, aka Bantam) project.[5] This engine was later known as the MC-1 engine when it was merged into the X-34 project.
The turbopump engine was designed to be used in an expendable booster in the LCBT project. As a result this led to the use of composite materials because of their significantly lower costs and production speed; this also reduced engine complexity since the fuel was not used for nozzle cooling. Based on knowledge and experience from the Space Shuttle's Reusable Solid Rocket Motor (RSRM) and the Solid Propulsion Integrity Program (SPIP),[6]aSilica/phenolic material was chosen for the ablative liner with carbon/epoxy structural overlap.
The engine fuel was a mixture of liquid oxygen and kerosene (RP-1). These propellants are used by Saturn F1 rocket engine. Kerosene does not have the same energy release as hydrogen, used with the Space Shuttle, but it is cheaper and easier to handle and store. Propellants were fed via a single shaft, dual impeller LOX/RP-1 turbo-pump.[7]
The engine was started with a hypergolic igniter to maintain a simple design. Kerosene was injected and the engine was then running. The propellants were then fed into the gas generator for mixing and thrust chamber for burning.
The engine uses a gas generator cycle to drive the turbo-pump turbine, which then exhausts this small amount of spent fuel. This is the identical cycle used with the Saturn rockets, but much less complex than the Space Shuttle engine system.
The engine used an inexpensive, expendable, ablatively cooled carbon fiber composite nozzle and produced 60,000 lbf (285 kN) of thrust. After use nearly all of the engine's parts are reusable.[8]
During the research phase in 1999 each Fastrac engine was costed at approximately $1.2 million.[9] Production costs were expected to drop to $350,000 per engine.
Engine system level testing started in 1999 at the Stennis Space Center.[10] Earlier tests were on individual components at the Marshall Space Flight Center. NASA started full-engine, hot-fire testing in March, 1999, with a 20 second test to demonstrate the complete engine system.[11] The engine was tested at full power for 155 seconds on July 1, 1999.[12] A total of 85 tests were scheduled for the rest of 1999. As of 2000, 48 tests had been conducted on three engines using three test stands.[13]
The first engine was installed on the X-34 A1 vehicle that was unveiled at NASA's Dryden Flight Research Center on April 30, 1999.[7]
The Fastrac program was cancelled in 2001.[4] After FASTRAC, 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 Marshall Center - 1 (MC-1). The MC-1 project was closed by July, 2009, after the X-34 project was terminated in March, 2009.[14]
NASA collaborated with industry partners to meet the principal objective to use commercial, off-the-shelf components. Industry partners included Summa Technology Inc., Allied Signal Inc., Marotta Scientific Controls Inc., Barber-Nichols Inc., and Thiokol Propulsion.
A similar set of technical solutions that reduce the cost of the engine was implemented in the SpaceX's Merlin 1A engine, which used a turbopump from the same subcontractor.[15] The Merlin-1A was somewhat larger with a thrust of 77,000 lbf (340 kN) versus 60,000 lbf (270 kN) for Fastrac. The same basic design was capable of much higher thrust levels after upgrading the turbopump. Variants of the Merlin-1D achieve 190,000 lbf (850 kN) of thrust as of May, 2018,[16] though the combustion chamber is now regeneratively cooled.[17]
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
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