Raptor 250 2012

Admin Desember 04, 2021

Raptor 250 2012

Family of cryogenic methane-fueled rocket engines developed by SpaceX

SpaceX Raptor
SpaceX sea-level Raptor at Hawthorne - 2.jpg
Country of origin United States
Manufacturer SpaceX
Status Currently in use
Liquid-fuel engine
Propellant Liquid oxygen / liquid methane
Mixture ratio 3.6 (78% O2, 22% CH4)[1] [2]
Cycle Full-flow staged combustion
Pumps 2 turbopumps
Configuration
Chamber 1
Nozzle ratio
  • 34.34 (sea-level),[3]
  • 80 (vacuum)[4]
Performance
Thrust ~185 tf (1.81 MN; 410,000 lbf) for Raptor 1
Throttle range 40–100%
Thrust-to-weight ratio
  • 200, sea-level, goal
  • <120, vacuum
Chamber pressure
  • 300 bar (4,400 psi)[5]
  • 330 bar (4,800 psi)~7s test
Specific impulse (vacuum) 378–380 s (3.71–3.73 km/s)
Specific impulse (sea-level) 330 s (3.2 km/s)[5]
Mass flow
  • ~650 kg/s (1,400 lb/s):[6]
    • ~510 kg/s (1,100 lb/s), O2 [7]
    • ~140 kg/s (310 lb/s), CH4 [7]
Dimensions
Length 3.1 m (10 ft)[8]
Diameter 1.3 m (4 ft 3 in)[9]
Dry weight 1,500 kg (3,300 lb), goal
Used in
SpaceX Starship

Raptor is a family of full-flow staged-combustion-cycle rocket engines developed and manufactured by SpaceX for use on the in-development SpaceX Starship. The engine is powered by "methalox" (cryogenic liquid methane and LOX) rather than the "kerolox" (RP-1 kerosene and LOX) used in SpaceX's prior Merlin and Kestrel rocket engines. The Raptor engine has more than twice the thrust of SpaceX's Merlin 1D engine that powers the Falcon 9 and Falcon Heavy launch vehicles.

Raptor is used in the Starship system in both the super-heavy-lift Super Heavy booster and in the Starship spacecraft which acts as the second stage when launched from Earth and as an independent spacecraft in LEO and beyond.[10] Starship is planned to be used in various applications, including Earth-orbit satellite delivery, deployment of a large portion of SpaceX's Starlink satellite constellation, exploration, Moon landing, and colonization of Mars.[11]

Development history [edit]

Conception and initial designs [edit]

An advanced rocket engine design project named Raptor, burning hydrogen and oxygen propellants, was first publicly discussed by SpaceX's Max Vozoff at the American Institute of Aeronautics and Astronautics Commercial Crew/Cargo symposium in 2009.[12] SpaceX had a few staff working on the Raptor upper-stage engine, then still a LH2 /LOX concept, at a low level of priority.[13] Further mention of the development program occurred in 2011.[14] In March 2012, news accounts asserted that the Raptor upper-stage engine development program was underway, but that details were not being publicly released.[15]

In October 2012, SpaceX publicly announced concept work on a rocket engine that would be "several times as powerful as the Merlin 1 series of engines, and won't use Merlin's RP-1 fuel", but declined to specify which fuel would be used.[16] They indicated that details on a new SpaceX rocket would be forthcoming in "one to three years" and that the large engine was intended for the next-generation launch vehicle using multiple of these large engines, that would be expected to launch payload masses of the order of 150 to 200 tonnes (150,000 to 200,000 kg; 330,000 to 440,000 lb) to low Earth orbit, exceeding the payload mass capability of the NASA Space Launch System by a wide margin.[16]

Development [edit]

Full flow staged combustion rocket diagram

In November 2012, Musk announced a new direction for the propulsion division of SpaceX which was towards developing methane-fueled rocket engines.[17] He further indicated that the Raptor concept would now become a methane-based design[17] and that methane would be the fuel of choice for SpaceX's plans for Mars colonization.[18] Because of the presence of water underground and carbon dioxide in the atmosphere of Mars, methane, a simple hydrocarbon, can easily be synthesized on Mars using the Sabatier reaction.[19] In-situ resource production on Mars has been examined by NASA and found to be viable for oxygen, water, and methane production.[20]

When first mentioned by SpaceX in 2009, the term "Raptor" was applied exclusively to an upper-stage engine concept[12]—and 2012 pronouncements indicated that it was then still a concept for an upper stage engine[21]—but in early 2014 SpaceX confirmed that Raptor would be used both on a new second stage, as well as for the large (then, nominally a 10-meter-diameter) core of the Mars Colonial Transporter[18] (subsequently, in 2016, on both stages of the Interplanetary Transport System[22] and then, in 2017 on the Big Falcon Rocket).[23]

Public information released in November 2012 indicated that SpaceX might have a family of Raptor-designated rocket engines in mind;[24] this was confirmed by SpaceX in October 2013.[11] However, in March 2014 SpaceX COO Gwynne Shotwell clarified that the focus of the new engine development program is exclusively on the full-size Raptor engine; smaller subscale methalox engines were not planned on the development path to the very large Raptor engine.[25]

In October 2013, SpaceX announced that they would be performing methane engine tests of Raptor engine components at NASA's John C. Stennis Space Center and that SpaceX would add equipment to the existing test stand infrastructure to support liquid methane and hot gaseous methane engine component testing.[26] [27] [28] In April 2014, SpaceX completed the requisite upgrades and maintenance to the Stennis test stand to prepare for testing of Raptor components,[29] and the engine component testing program began in earnest, focusing on the development of robust startup and shutdown procedures. Component testing at Stennis also allowed hardware characterization and verification.[30]

SpaceX successfully began development testing of injectors in 2014 and completed a full-power test of a full-scale oxygen preburner in 2015. 76 hot-fire tests of the preburner, totaling some 400 seconds of test time, were executed from April–August 2015.[31] SpaceX completed its planned testing using NASA Stennis facilities in 2014 and 2015.[32]

In January 2016, the US Air Force awarded a US$33.6 million development contract to SpaceX to develop a prototype version of its methane-fueled reusable Raptor engine for use on the upper stage of the Falcon 9 and Falcon Heavy launch vehicles, which required double-matching funding by SpaceX of at least US$67.3 million.[ citation needed ] Work under the contract was expected to be completed in 2018, with engine performance testing to be done at Stennis Space Center and at Los Angeles Air Force Base, California.[33] [34]

Testing [edit]

First test firing of a Raptor development engine on 25 September 2016 in McGregor, Texas

Initial development testing[31] of Raptor methane engine components was done at NASA's Stennis Space Center, where SpaceX added equipment to the existing infrastructure to support liquid methane engine testing.[11] [28]The development Raptor engine discussed in the October 2013 time frame relative to Stennis testing was designed to generate more than 2,900 kN (661,000 lbf) vacuum thrust.[11] Raptor engine component testing began in May 2014 at the E-2 test complex which SpaceX modified to support methane engine tests.[11] [29] SpaceX completed a "round of main injector testing in late 2014" and a "full-power test of the oxygen preburner component" for Raptor by June 2015.[ citation needed ]

By early 2016, SpaceX had constructed a new engine test stand at their McGregor test site in central Texas for Raptor testing.[30] [11] By August 2016, the first integrated Raptor rocket engine, manufactured at the SpaceX Hawthorne facility in California, was shipped to SpaceX McGregor for development testing.[35] The engine had 1 MN (220,000 lbf) thrust, less than half the thrust of the full-scale Raptor engine used for flight tests in 2019.[36] It is the first full-flow staged-combustion methalox engine ever to reach a test stand.[30] It performed an initial 9-second firing test on 26 September 2016, the day before Musk's talk at the International Aeronautical Congress.[ citation needed ]

On 26 September 2016, Elon Musk disclosed that the engine used multi-stage turbopumps. Substantial additional technical details of the ITS propulsion were summarized in an article on the Raptor engine published the next week.[30] In September 2016, at the 67th International Astronautical Congress, Musk mentioned several Raptor engine designs that were planned for the Interplanetary Transport System.[ citation needed ] In addition, a much smaller subscale development engine had already been built for design validation. At that time, this first subscale Raptor development engine had recently been tested on a ground test stand in McGregor, but for only one brief firing.[30] [ citation needed ] The Raptor subscale development engine produced approximately 1,000 kN (220,000 lbf) thrust.[30] [ citation needed ] To eliminate flow separation problems while being tested in Earth's atmosphere, the test nozzle expansion ratio had been limited to 150. NASASpaceFlight reported that the development engine was only one-third the size of any of the several larger engine designs that were discussed for the later flight vehicles.[30] [ citation needed ]

By September 2017, the development Raptor engine—with 200 bars (20 MPa; 2,900 psi) chamber pressure—had undergone 1200 seconds of test fire testing in ground-test stands across 42 main engine tests, with the longest test being 100 seconds, which is limited by the capacity of the ground-test propellant tanks.[ citation needed ] The first version of the flight engine is intended to operate at a chamber pressure of 250 bars (25 MPa; 3,600 psi), with the intent to raise it to 300 bars (30 MPa; 4,400 psi) at a later time.[37] By September 2017, the 200 bars (20 MPa; 2,900 psi) sub-scale test engine, with a thrust of 1 meganewton (220,000 lbf) and "a new alloy to help its oxygen-rich turbopump resist oxidization, ... had completed 1200 seconds of firings across 42 tests."[38] This alloy is known as SX500, created by the SpaceX metallurgy team which is used to contain hot oxygen gas in the engine at up to 12000 psi.[ citation needed ]

Applications for Big Falcon Rocket [edit]

Big Falcon Rocket with its Super Heavy booster firing (artist's concept)

While plans for Raptor flight testing have consistently been on the new-generation fiber-composite-material construction flight vehicles since 2016, the specific vehicle was not clarified until October 2017, when it was indicated that initial suborbital test flights would occur with a Big Falcon Ship.[39] In November 2016, the first flight tests of the Raptor engine were projected to be on the Interplanetary Transport System, no earlier than the early 2020s.[30] By July 2017, the plan had been modified to do flight testing on a much smaller launch vehicle and spacecraft, and the new system architecture had "evolved quite a bit" since the ITS concept in 2016.[ citation needed ] A key driver of the 2017 architecture was to make the new system useful for substantial Earth-orbit and cislunar launches so that the new system might pay for itself, in part, through economic spaceflight activities in the near-Earth space zone.[40]

Elon Musk announced in September 2017 that the initial flight platform for any Raptor engine would be some part of the Big Falcon Rocket.[ citation needed ] BFR was a 9 m (30 ft)-diameter launch vehicle.[37] In October 2017, Musk clarified that "[initial flight testing will be with] a full-scale 9-meter-diameter ship doing short hops of a few hundred kilometers altitude and lateral distance ... [projected to be] fairly easy on the vehicle, as no heat shield is needed, we can have a large amount of reserve propellant and don't need the high area ratio, deep-space Raptor engines."[39]

For the flight vehicles, Elon Musk discussed two engines: a sea-level variant (expansion ratio 40:1) for the first stage or ITS booster and a vacuum variant (expansion ratio 200:1) to obtain higher performance with the second stage. 42 of these sea-level engines were envisioned in the high-level design of the first stage, with a thrust per engine of 3,050 kN (690,000 lbf) at sea level and 3,285 kN (738,000 lbf) in the vacuum.[30] In addition, three gimbaled sea-level Raptor engines would be used for performing landings of the ITS second stage on Earth and Mars. Six vacuum-optimized Raptor engines, providing 3,500 kN (790,000 lbf) of thrust each, would also be used on the ITS second stage, for a total of nine engines.[ citation needed ] The higher-efficiency Raptor Vacuum engines for in-space conditions were envisioned then to target a specific impulse of 382s, using a much larger nozzle giving an expansion ratio of 200.[41] Six of these non-gimbaled engines were planned to provide primary propulsion for the 2016 designs of the ITS second stage.[30]

A year later, at the 68th IAC in September 2017, and following a year of development by the propulsion team, Musk said that a smaller Raptor engine—with slightly over half as much thrust as the previous concept designs for the ITS — would be used on the next-generation rocket, now a 9 m (30 ft)-diameter launch vehicle and publicly referred to as Big Falcon Rocket (BFR).[ citation needed ] With the much smaller launch vehicle, fewer Raptor engines would be used on each stage. BFR was then slated to have 31 Raptors on the first stage and 6 on the second stage.[42] [30] By mid-2018, SpaceX was publicly stating that the sea-level flight version Raptor engine design, with a nozzle exit diameter of 1.3 m (4.3 ft), was expected to have 1,700 kN (380,000 lbf) thrust at sea level with a specific impulse of 330 s (3,200 m/s) increasing to a specific impulse of 356 s (3,490 m/s) in vacuum.[38] The vacuum flight version, with a nozzle exit diameter of 2.4 m (7.9 ft), was expected to exert 1,900 kN (430,000 lbf) force with a specific impulse of 375 s (3,680 m/s).[38] The earliest versions of the flight engine are designed to operate at 250 bars (25,000 kPa; 3,600 psi) chamber pressure; but SpaceX is expected to increase this to 300 bar (30,000 kPa; 4,400 psi) in later iterations.[38]

In the BFR update given in September 2018, Musk showed a video of a 71-second fire test of a Raptor engine, and stated that "this is the Raptor engine that will power BFR, both the ship and the booster; it's the same engine. ... approximately a 200 (metric) tons engine aiming for roughly 300 bar chamber pressure. ... If you had it at a high expansion ratio, has the potential to have a specific impulse of 380."[5]

Renaming from BFR to Starship [edit]

In November 2018, SpaceX began referring to its vehicle using new names instead of BFR: Super Heavy for the booster, Starship for the spacecraft, and Starship system or just Starship for the whole vehicle.[43]

Production [edit]

In July 2021, SpaceX announced that they would be building a second production facility for Raptor engines, this one in south Texas near the existing rocket engine test facility. Dallas Morning News reported in July that SpaceX will "break ground soon" and that the facility will concentrate on the serial production of Raptor 2, while the California facility will produce Raptor Vacuum and new/experimental Raptor designs. The new facility is expected to eventually produce 800 to 1000 rocket engines each year.[44] [45] SpaceX aims at a lifetime of 1000 flights for Raptor.[46] In 2019 the (marginal) cost of the engine was stated to be approaching $1 million. SpaceX plans to mass-produce up to 500 Raptor engines per year, each costing less than $250,000. Each Starship booster will use 33 sea-level Raptors, while each Starship spacecraft will use 3 sea-level Raptors plus 3 Vacuum-optimized Raptors.[ citation needed ]

Raptor Vacuum [edit]

Raptor Vacuum[47] (also RVac) is a variant of Raptor with an extended, regeneratively-cooled nozzle for higher specific impulse in the vacuum of space. While the optimized Raptor vacuum engine is aiming for a specific impulse of ~380 s (3,700 m/s),[48] the v1.0 Raptor vac design to support early Starship development has been made more conservative and is projecting a specific impulse of only 365–370 s (3,580–3,630 m/s), intentionally decreasing engine performance to obtain test engines sooner.[ citation needed ] In addition, Raptor Vacuum v1 will have a smaller engine nozzle to avoid flow separation when the engine is fired at sea-level atmospheric pressure.[ citation needed ] A full-duration test of version 1 of the Raptor Vacuum engine was completed in September 2020 at the SpaceX development facility in McGregor, Texas.[47] The first three operational Raptor Vacuum engines will be flown on SpaceX Starship prototype S20 and were installed on the 4th of August 2021.[49]

Raptor 2 [edit]

Raptor 2 is the post-iterative-development version of Raptor.[ citation needed ] In September 2019, SpaceX stated their "current plan" was to use Raptor 2 for the three "sea-level" engines on the Starship second-stage and also for all booster engines — both those that gimbal and those that do not — on the Super Heavy first stage.[50] Currently, no Raptor 2 engines had flown on the various Starship prototype vehicles.[ citation needed ] These engines will eventually be produced at SpaceX's new engine development facility near McGregor, Texas announced in July 2021; no date has yet been made public as to when the facility might be operational for production.[ citation needed ]

Components [edit]

Raptor engine combustion scheme

The Raptor engine is powered by subcooled liquid methane and subcooled liquid oxygen in a full-flow staged combustion cycle, a departure from the simpler "open-cycle" gas generator system and LOX/kerosene propellants that current Merlin engines use.[21] The RS-25, first used on the Space Shuttle, uses a simpler form of a staged combustion cycle,[51] as do several Russian rocket engines, including the RD-180[21] and the RD-191.[30]

The Raptor engine is designed for the use of deep cryogenic propellants—fluids cooled to near their freezing points, rather than using the cryo-propellants at their boiling points as it is more typical for cryogenic rocket engines.[52] The use of subcooled propellants increases propellant density to allow more propellant mass to be stored within the vehicle's tanks[ citation needed ]. Engine performance is also increased with subcooled propellants.[ citation needed ] Specific impulse is increased, and the risk of cavitation at inputs to the turbopumps is reduced due to the higher propellant fuel mass flow rate per unit of power generated.[30] The oxidizer to fuel ratio of the engine would be approximately 3.8 to 1, as stated by Elon Musk.[53]

Musk revealed that their target performance for Raptor was a vacuum specific impulse of 382 s (3,750 m/s), with a thrust of 3 MN (670,000 lbf), a chamber pressure of 300 bar (30 MPa; 4,400 psi), and an expansion ratio of 150 for the vacuum-optimized variant.[ citation needed ]

Engine ignition for all Raptor engines, both on the pad and in the air, is handled by dual-redundant spark-plug lit torch igniters,[54] eliminating the need for a dedicated, consumable igniter fluid, as used on Merlin.[30]

Raptor has been claimed to be able to deliver "long life ... and more benign turbine environments".[55] [30] Specifically, Raptor utilizes a full-flow staged combustion cycle, where all the oxygen will power an oxygen turbopump, and all the fuel will power a methane turbopump. Both streams—oxidizer and fuel—will be mixed completely in the gas phase before they enter the combustion chamber.[ citation needed ] Before 2014, only two full-flow staged-combustion rocket engine designs had ever progressed sufficiently to be tested on test stands: the Soviet RD-270 project in the 1960s and the Aerojet Rocketdyne Integrated Powerhead Demonstrator in the mid-2000s.[56] [30] [18] The flight engine is designed for extreme reliability, aiming to support the airline-level of safety required by the point-to-point Earth transportation market.[39]

Many components of early Raptor prototypes were manufactured using 3D printing, including turbopumps and injectors, with the effect of increasing the speed of development and iterative testing.[52] The 2016 subscale development engine had 40% (by mass) of its parts manufactured by 3D printing.[30] In 2019, engine manifolds were cast from SpaceX's in-house developed SX300 Inconel superalloy, soon to be changed to SX500.[57] The Raptor engine uses a large number of coaxial swirl injectors to admit propellants to the combustion chamber, rather than pintle injectors used on the previous Merlin rocket engines that SpaceX mass-produced for its Falcon family of launch vehicles.[58] [ citation needed ]

Usage in launch vehicles [edit]

SpaceX Starship [edit]

Starship SN20 has its tiles inspected

Thirty-three sea-level variant Raptor engines will power the Super Heavy booster, while the Starship spacecraft contains six Raptor engines, three optimized for sea‑level and three optimized for vacuum.[59] The bottom-most section, informally called the "skirt", houses the Raptor engines, as well as composite overwrapped pressure vessels that store helium gas used to spin up the Raptor turbopumps.[60] Above that section are the liquid oxygen and liquid methane propellant tanks, separated by a "common dome" containing a small, spherical methane "header tank" used to contain propellant for landing.[61] [62] Six Raptor engines power the spacecraft, three designed for sea-level operation and three Raptor Vacuum engines optimized for use in the vacuum of space, producing a cumulative thrust of about 14 MN (1,400 tf; 3,100,000 lbf).[63]

Proposed Falcon 9 upper stage [edit]

In January 2016, the United States Air Force (USAF) awarded a US$33.6 million development contract to SpaceX to develop a prototype version of its methane-fueled reusable Raptor engine for use on the upper stage of the Falcon 9 and Falcon Heavy launch vehicles. The contract required double-matching funding by SpaceX of at least US$67.3 million.[33] [64] Work under the contract was expected to be completed no later than December 2018, and engine performance testing was planned to be completed at NASA's Stennis Space Center in Mississippi under US Air Force supervision.[33] [34] The USAF contract called only for the development and build of a single prototype engine with a series of ground tests, with no upper-stage launch vehicle design funded by the contract.[33] The Air Force was working with the US Congress in February 2016 to pursue new launch systems.[65]

In October 2017 the US Air Force (USAF) awarded a US$40.8 million modification for the development of the Raptor engine prototype for the Evolved Expendable Launch Vehicle program, with work under that contract expected to be completed by April 2018.[66]

Little technical detail was ever publicly released about the USAF second stage engine. The prototype however was to be designed to serve the theoretical purpose of servicing an upper stage that could be used on the existing Falcon 9 and Falcon Heavy launch vehicles, with liquid methane and liquid oxygen, propellants, a full-flow staged combustion cycle, and explicitly to be a reusable engine.[34]

The USAF contract called only for the development and build of a prototype, to be demonstrated in a USAF-supervised set of tests. No upper-stage vehicle design/redesign was funded by the contract.[33] Neither the Air Force nor SpaceX subsequently published any results of this non-Starship-oriented rocket engine contract.[ citation needed ]

Comparison to other engines [edit]

Engine Rockets Thrust Specific impulse,

vacuum

Thrust-to-

weight ratio

Propellant Cycle
Raptor sea-level Starship 2,200 kN (500,000 lbf)[36] ~350 s (3,400 m/s)[67] 200 (goal) LCH4 / LOX Full-flow staged combustion
Raptor vacuum ~380 s (3,700 m/s)[67] <120
Merlin 1D sea-level Falcon booster stage 914 kN (205,000 lbf) 311 s (3,050 m/s)[68] 176[69] RP-1 / LOX

(subcooled)

Gas generator
Merlin 1D vacuum Falcon upper stage 934 kN (210,000 lbf)[70] 348 s (3,410 m/s)[70] 180[69]
Blue Origin BE-4 New Glenn, Vulcan 2,400 kN (550,000 lbf)[71] LNG / LOX Oxidizer-rich staged combustion
Energomash RD-170/171M Energia, Zenit, Soyuz-5 7,904 kN (1,777,000 lbf)[72] 337.2 s (3,307 m/s)[72] 79.57[72] RP-1 / LOX
Energomash RD-180 Atlas III, Atlas V 4,152 kN (933,000 lbf)[73] 338 s (3,310 m/s)[73] 78.44[73]
Energomash RD-191/181 Angara, Antares 2,090 kN (470,000 lbf)[74] 337.5 s (3,310 m/s)[74] 89[74]
Kuznetsov NK-33 N1, Soyuz-2-1v 1,638 kN (368,000 lbf)[75] 331 s (3,250 m/s)[75] 136.66[75]
Energomash RD-275M Proton-M 1,832 kN (412,000 lbf) 315.8 s (3,097 m/s) 174.5 N2O4 / UDMH
Rocketdyne RS-25 Space Shuttle, SLS 2,280 kN (510,000 lbf) 453 s (4,440 m/s)[76] 73[77] LH2 / LOX Fuel-rich staged combustion
Aerojet Rocketdyne RS-68A Delta IV 3,560 kN (800,000 lbf) 414 s (4,060 m/s) 51[78] LH2 / LOX Gas generator
Rocketdyne F-1 Saturn V 7,740 kN (1,740,000 lbf) 304 s (2,980 m/s)[79] 83 RP-1 / LOX Gas generator

See also [edit]

  • Comparison of orbital rocket engines
  • SpaceX Mars program
  • SpaceX rocket engines
  • SpaceX Starship
  • SpaceX Starship development history

References [edit]

  1. ^ Sierra Engineering & Software, Inc. (18 June 2019). "Exhaust Plume Calculations for SpaceX Raptor Booster Engine" (PDF). p. 1. Retrieved 17 September 2021. The nominal operating condition for the Raptor engine is an injector face stagnation pressure (Pc) of 3669.5 psia and a somewhat fuel-rich engine O/F mixture ratio (MR) of 3.60. The current analysis was performed for the 100% nominal engine operating pressure (Pc=3669.5 psia) and an engine MR of 3.60.
  2. ^ Space Exploration Technologies Corp. (17 September 2021). "Draft Programmatic Environmental Assessment for the SpaceX Starship/Super Heavy Launch Vehicle Program at the SpaceX Boca Chica Launch Site in Cameron County, Texas" (PDF). faa.gov. FAA Office of Commercial Space Transportation. p. 12. Archived (PDF) from the original on 17 September 2021. Retrieved 17 September 2021. Super Heavy is expected to be equipped with up to 37 Raptor engines, and Starship will employ up to six Raptor engines. The Raptor engine is powered by liquid oxygen (LOX) and liquid methane (LCH4) in a 3.6:1 mass ratio, respectively.
  3. ^ Sierra Engineering & Software, Inc. (18 June 2019). "Exhaust Plume Calculations for SpaceX Raptor Booster Engine" (PDF). p. 1. Retrieved 17 September 2021. The subject engine uses a closed power cycle with a 34.34:1 regeneratively-cooled thrust chamber nozzle.
  4. ^ "Starbase Tour with Elon Musk [PART 2]" on YouTube by Everyday Astronaut, Aug 7, 2021
  5. ^ a b c Musk, Elon (17 September 2018). "First Lunar BFR Mission". YouTube. Event occurs at 45:30. Archived from the original on 11 February 2020. Retrieved 19 September 2018. And this is the Raptor engine that will power BFR both the ship and the booster, it's the same engine. And this is approximately a 200-ton thrust engine that's aiming for roughly a 300-bar or 300-atmosphere chamber pressure. And if you have it at a high expansion ratio it has the potential to have a specific impulse of 380.
  6. ^ At 2.23MN thrust and 350s specific impulse
  7. ^ a b 78% O2, 22% CH4 mixture ratio
  8. ^ "Archived copy". Archived from the original on 30 September 2019. Retrieved 2 October 2019. CS1 maint: archived copy as title (link)
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External links [edit]

  • SpaceX Raptor Engine Test on 25 September 2016, SciNews, video, September 2016.
  • GPUs to Mars: Full-scale Simulation of SpaceX's Mars Rocket Engine, Adam Lichtl and Steven Jones, GPU Technology Conference, spring 2015.
  • unofficial raptor engine log infographic

Raptor 250 2012

Source: https://en.wikipedia.org/wiki/SpaceX_Raptor

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