Merlin (rocket engine family)
Test firing at SpaceX McGregor's test stand of the Merlin 1D
|Country of origin||United States|
|Application||Falcon 9, Falcon Heavy|
|Propellant||LOX / RP-1 (rocket grade kerosene)|
|Thrust (vac.)||720 kN (161,000 lbf)|
|Thrust (SL)||650 kN (147,000 lbf)|
|Chamber pressure||9.7 MPa (1,410 psi)|
|Isp (vac.)||311 s (3.0 km/s)|
|Isp (SL)||282 s (2.73 km/s)|
Merlin is a family of rocket engines developed by SpaceX for use on its Falcon 1 and Falcon 9 launch vehicles. SpaceX also plans to use Merlin engines on its Falcon Heavy. Merlin engines use RP-1 and liquid oxygen as propellants in a gas-generator power cycle. The Merlin engine was originally designed for sea recovery and reuse.
Propellants are fed via a single shaft, dual impeller turbo-pump. The turbo-pump also provides high pressure fluid for the hydraulic actuators, which then recycles into the low pressure inlet. This eliminates the need for a separate hydraulic power system and means that thrust vector control failure by running out of hydraulic fluid is not possible. A third use of the turbo-pump is to provide power to pivot the turbine exhaust nozzle for roll control purposes.
Three versions of the Merlin 1C engine have been produced. The Merlin engine for Falcon 1 had a movable turbo-pump exhaust assembly which was used to provide roll control by vectoring the exhaust. The Merlin 1C engine for the Falcon 9 first stage is nearly identical to the variant used for the Falcon 1 except that the turbo-pump exhaust assembly is not movable. Finally, a Merlin 1C vacuum variant is used on the Falcon 9 second stage. This engine differs from the Falcon 9 first stage variant in that it uses a larger exhaust nozzle optimized for vacuum operation and can be throttled between 60 and 100 percent.
Merlin 1A 
The initial version, the Merlin 1A, used an inexpensive, expendable, ablatively cooled carbon fiber composite nozzle, and produced 340 kN (77,000 lbf) of thrust. The Merlin 1A flew only two times: First on 24 March 2006, when it caught fire and failed due to a fuel leak shortly after launch, and the second time on 21 March 2007, where it performed successfully. Both times the Merlin 1A was mounted on a Falcon 1 first stage.
The SpaceX turbopump was an entirely new, clean sheet design contracted to Barber-Nichols Inc in 2002 who performed all design, engineering analysis and construction. Barber-Nichols Inc. applied lessons learned from the RS-88 (Bantum) and NASA Fastrac engine programs for their turbopump products. The Merlin 1A turbopump uses a unique friction welded main shaft (inconel 718 ends with an integral aluminum RP-1 impeller in the middle). The turbopump housing is constructed of investment castings (inconel at the turbine end, aluminum in the center, and 300-series stainless steel at the LOX end). The turbine is a partial-admission impulse design and turns at 20,000 rpm. Total turbopump weight was 150-lbs.
Merlin 1B 
The Merlin 1B rocket engine was an upgraded version of the Merlin 1A engine. The turbopump upgrades were handled by Barber-Nichols Inc for SpaceX. It was intended for Falcon 1 launch vehicles, capable of producing 380 kN (85,000 lbf) of thrust. The Merlin 1B was enhanced over the 1A with a turbine upgrade (from 1490 kW to 1860 kW). The turbine upgrade was accomplished by adding additional nozzles (turning the previous partial-admission design to full-admission). Slightly enlarged impellers for both RP-1 and LOX were part of the upgrade. This model turned at a faster 22,000 rpm and developed higher discharge pressures. Turbopump weight was unchanged at 150 lbs.
Initial use of the Merlin 1B was to be on the Falcon 9 launch vehicle, on whose first stage there would have been a cluster of nine of these engines. Due to experience from the Falcon 1's first flight, the 1B was never used on a flight vehicle. SpaceX moved its Merlin development to the Merlin 1C, which is regeneratively cooled. Therefore the Merlin 1B was never in use on a launch vehicle.
Merlin 1C 
Merlin 1C under construction at SpaceX factory
|Country of origin||United States|
|Propellant||LOX / RP-1 (rocket grade kerosene)|
|Thrust (vac.)||480 kN (110,000 lbf)|
|Thrust (SL)||420 kN (94,000 lbf)|
|Chamber pressure||6.77 MPa (982 psi)|
|Isp (vac.)||304.8 s (3.0 km/s)|
|Isp (SL)||275 s (2.6 km/s)|
|Length||2,920 mm (115 in)|
|Diameter||1,676 mm (66.0 in)|
|Dry weight||1,380 pounds (630 kg)|
The Merlin 1C uses a regeneratively cooled nozzle and combustion chamber. The turbopump used is a Merlin 1B model with only slight alterations. It was fired with a full mission duty firing of 170 seconds in November, 2007, first flew on a mission in August 2008, powered the "first privately-developed liquid-fueled rocket to successfully reach orbit", Falcon 1 Flight 4, in September 2008, and powered the Falcon 9 on its maiden flight in June 2010.
As configured for use on Falcon 1 vehicles, the Merlin 1C had a sea level thrust of 350 kN (78,000 lbf), a vacuum thrust of 400 kN (90,000 lbf) and a vacuum specific impulse of 304 seconds. In this configuration the engine consumed 140 kg (300 lb) of propellant per second. Tests have been conducted with a single Merlin 1C engine successfully running a total of 27 minutes (counting together the duration of the various tests), which equals ten complete Falcon 1 flights. The Merlin 1C chamber and nozzle are cooled regeneratively by 100 pounds (45 kg) per second of kerosene flow, and are able to absorb 10 megawatts (13,000 hp) of thermal heat energy.
A Merlin 1C was first used as part of the unsuccessful third attempt to launch a Falcon 1. In discussing the failure, Elon Musk noted, "The flight of our first stage, with the new Merlin 1C engine that will be used in Falcon 9, was picture perfect." The Merlin 1C was used in the successful fourth flight of Falcon 1 on September 28, 2008.
On October 7, 2012 a Merlin 1C (Engine No. 1) of the CRS-1 mission experienced an anomaly at T+00:01:20 which appears on CRS-1 launch video as a flash. Failure occurred just as the vehicle achieved Max-Q (maximum aerodynamic pressure). SpaceX's internal review found that the engine was shut down after a sudden pressure loss, and that only the aerodynamic shell was destroyed, generating the debris seen in the video. The engine itself did not explode, as SpaceX ground control continued to receive data from it throughout the flight. The primary mission was unaffected by the anomaly due to the nominal operation of the remaining eight engines and an onboard readjustment of the flight trajectory, but the secondary mission payload failed to achieve orbit due to safety protocols in place to prevent collisions with the ISS.
SpaceX was planning to develop a 125000 lbf version of Merlin 1C to be used in Falcon 9 block II and Falcon 1E boosters. This engine and these booster models were dropped in favour of more advanced Merlin 1D engine and longer Falcon 9 v1.1 booster.
Merlin Vacuum (1C) 
On March 10, 2009 a SpaceX press release announced successful testing of the Merlin Vacuum engine. A variant of the 1C engine, Merlin Vacuum features a larger exhaust section and a significantly larger expansion nozzle to maximize the engine's efficiency in the vacuum of space. Its combustion chamber is regeneratively cooled while the 2.7 metres (9 ft)-long niobium alloy expansion nozzle is radiatively cooled. The engine delivers a vacuum thrust of 411 kN (92,500 lbf) and a vacuum specific impulse of 342 seconds. The first production Merlin Vacuum engine underwent a full duration orbital insertion firing (329 seconds) of the integrated Falcon 9 second stage on January 2, 2010. It was flown on the second stage for the inaugural Falcon 9 flight on June 4, 2010. At full power the Merlin Vacuum engine operates with the greatest efficiency ever for an American-made hydrocarbon rocket engine.
An interesting unplanned test of a modified Merlin Vacuum engine was made in December 2010. Shortly before the scheduled second flight of the Falcon 9, two cracks were discovered in the 2.7 metres (9 ft)-long niobium-alloy-sheet nozzle of the Merlin Vacuum engine. The engineering solution was to cut off the lower 1.2 metres (4 ft) of the nozzle, and launch two days later, as the extra performance that would have been gained from the longer nozzle was not necessary to meet the objectives of the mission. Even with the shortened nozzle, the engine placed the second-stage into an orbit of 11,000 kilometres (6,800 mi) altitude.
Merlin 1D 
The Merlin 1D engine was developed by SpaceX in 2011–2012, with first flight scheduled for 2013. The Merlin 1D was originally (April 2011) designed for a sea level thrust of 620 kN (140,000 lbf). At the 2011 AIAA Propulsion Conference, SpaceX's Tom Mueller revealed that the engine would have a vacuum thrust of 690 kN (155,000 lbf), a vacuum specific impulse (Isp) of 310 s, an increased expansion ratio of 16 (as opposed to the previous 14.5 of the Merlin 1C) and chamber pressure in the "sweet spot" of 9.7 MPa (1,410 psi). A new feature for the engine is the ability to throttle from 100% to 70%.
The design goals for the new engine design included increased reliability (increased fatigue life and increased chamber and nozzle thermal margins), improved performance (thrust design objective 140,000 pounds-force (620 kN) and 70-100 percent throttle capability), and improved manufacturability (lower parts count and fewer labor hours). The engine's 150:1 thrust-to-weight ratio would be the highest ever achieved for a rocket engine.
When testing was completed in June 2012, SpaceX stated that the engine had completed a full mission duration test firing of 185 seconds delivering 650 kN (147,000 lbf) of thrust and also confirming the expected thrust-to-weight ratio exceeding 150. As of November 2012 the Falcon 9's page Merlin section describes the characteristics as having a sea level thrust of 650 kN (147,000 lbf), a vacuum thrust of 720 kN (161,000 lbf), a sea level specific impulse (Isp) of 282 s and a vacuum specific impulse (Isp) of 311 s. The engine has the highest specific impulse ever achieved for a gas-generator cycle kerosene rocket engine. On March 20, 2013 SpaceX announced the Merlin 1D engine has achieved flight qualification.
The first flight of the Falcon 9 with Merlin 1D engines will be the CASSIOPE "800 pounds (360 kg) weather research and communications satellite, launched into a highly elliptical low Earth orbit (LEO) for the Canadian Space Agency." The second flight will be the geosynchronous transfer orbit (GTO) launch of SES-8 in July 2013.
Merlin Vacuum (1D) 
A vacuum version of the Merlin 1D engine is planned for the Falcon Heavy second stage. On 30 September 2012 Elon Musk tweeted an image of the Merlin 1D-Vac firing on the test stand and stated "Now test firing our most advanced engine, the Merlin 1D-Vac, at 80 tons of thrust."  It generated significant speculation because the "tons" could mean either US short tonnes (which, at 710 kN (160,000 lbf), roughly corresponds with the vacuum thrust of the stock Merlin 1D) or metric tonnes (which would imply a significantly more powerful 785 kN (176,400 lbf) thrust that would be expected from a bigger radiatively cooled nozzle like the Merlin 1C-Vac. Some speculation is also made in the analysis of the picture which apparently would show the tubing of the gas generator exhaust into a hot manifold which would pass the gases to the inner walls of the nozzle extension, providing a sort of curtain cooling not unlike the Rocketdyne F-1 engine.
Engine control 
SpaceX uses a triple-redundant design in the Merlin flight computers. The system utilizes three computers in each processing unit, each constantly checking on the others, to instantiate a fault-tolerant design. One processing unit is part of each of the ten Merlin engines (nine on first stage, one on second stage) used on a Falcon 9 launch.
Future engines 
SpaceX has both other main-engine development programs underway and has also released to the public details on future engine concepts. The concepts have included liquid hydrogen (LH2) fueled engines in addition to SpaceX' Merlin family of RP1-fueled engines currently in production. However, in November 2012, SpaceX CEO Elon Musk announced a new direction for propulsion side of the company: developing methane/LOX rocket engines, which have cost advantages and a slight Isp advantage over Kerosene while avoiding adverse aspects of liquid hydrogen technology.
Merlin 2 concept 
At the AIAA Joint Propulsion conference on July 30, 2010 SpaceX McGregor rocket development facility director Tom Markusic shared some information from the initial stages of planning for a new engine. SpaceX’s Merlin 2 LOX/RP-1-fueled engine on a gas generator cycle, capable of a projected 7,600 kN (1,700,000 lbf) of thrust at sea level and 8,500 kN (1,920,000 lbf) in a vacuum and would provide the power for conceptual super-heavy-lift launch vehicles from SpaceX, which Markusic dubbed Falcon X and Falcon XX. Such a capability would result in an engine with more thrust than the F-1 engines used on the Saturn V.
Slated to be introduced on more capable variants of the Falcon 9 Heavy, the Merlin 2 "could be qualified in three years for $1 billion", Markusic says. By mid-August, the SpaceX CEO Elon Musk clarified that while the Merlin 2 engine architecture was a key element of any effort SpaceX would make toward their objective of "super-heavy lift" launch vehicles—and that SpaceX did indeed want to "move toward super heavy lift"—the specific potential design configurations of the particular launch vehicles shown by Markusic at the propulsion conference were merely conceptual "brainstorming ideas", just a "bunch of ideas for discussion."
Merlin 1C engine specifications 
- Sea level thrust: 556 kN (125,000 lbf)
- Vacuum thrust: 616 kN (138,400 lbf)
- Sea level specific impulse: 275 s (2.6 kN·s/kg)
- Vacuum specific impulse: 304 s (3.0 kN·s/kg)
- Fuel: RP-1 (rocket grade kerosene)
- Oxidizer: liquid oxygen
- Chamber pressure: 6.77 MPa (982 psi)
- Thrust-to-weight ratio (fully accounted): 96
See also 
|Wikimedia Commons has media related to: Merlin (rocket engine)|
- Draco (rocket engine) – SpaceX RCS thruster.
- Kestrel (rocket engine) – SpaceX small upper stage engine for Falcon 1.
- Falcon (rocket family) - SpaceX rockets exclusively using LOX/RP-1 launch vehicle engines.
- Raptor (rocket engine) - SpaceX methane/LOX engine
- SpaceX MCT - SpaceX next generation engine concept.
- Comparison of orbital rocket engines
- Rocket engine
- Pintle injector
- TR-106 - Low Cost Pintle Engine (LCPE) using LOX/LH2 developed by TRW in 2000.
- TR-107 - RP1 engine developed under SLI for future reusable launch vehicles.
- RS-27A – RP-1 engine used in the US Delta II launcher; Saturn 1B H-1 heritage.
- RD-171 - RP-1 engine currently used on the Zenit launcher.
- RD-180 – RP-1 engine currently used in the first-stage of the US Atlas V launcher.
- RD-191 – contemporary Russian RP-1 engine, to be used on the Angara launchers.
- NK-33 – RP-1 engine developed for the Soviet N1 moon rocket, currently slated for use on the Soyuz-1 and by Orbital Sciences in the Antares launcher.
- F-1 (rocket engine) – LOX/RP-1 main engine of the Saturn V moon rocket.
- Executor (rocket engine)
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