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Space Launch System

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This is an old revision of this page, as edited by 65.110.28.47 (talk) at 19:25, 2 August 2019 (→Current SLS: First static firing delayed until 2020, means that earliest launch no earlier than 2021.). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.

This article is about the NASA rocket family. For the similarly-named US Air Force project of the 1960s, see Space Launching System. For Turkey's UFS satellite launcher, see Space Launch System (Turkey).

Space Launch System
Artist's rendering of SLS Block 1/Orion
FunctionSuper heavy-lift launch vehicle
Country of originUnited States
Project costUS$7 billion (2014–18, 2014 estimate),[1] to
$35 billion (until 2025, 2011 est.)[2][3][better source needed]
Size
Height111.25 m (365 ft 0 in), Block 2 Cargo
Diameter8.4 m (27 ft 7 in), Core Stage
Stages2
Capacity
Payload to LEO
Mass
  • Block 1: 95 t (209,000 lb)[4]
  • Block 2: 130 t (290,000 lb)[5]
Payload to Moon
Mass
  • Block 1: > 26,000 kg (57,000 lb)[6]
  • Block 1B Crew: 34,000–37,000 kg (75,000–82,000 lb)[6]
  • Block 1B Cargo: 37,000–40,000 kg (82,000–88,000 lb)[6]
  • Block 2: > 45,000 kg (99,000 lb)[6]
Launch history
StatusUnder development
Launch sitesLC-39B, Kennedy Space Center
First flightArtemis 1
June 2020 (planned)[7]
Type of passengers/cargoOrion MPCV, Europa Clipper, LOP-Gateway Station components
Boosters (Block 1, 1B)
No. boosters2 five-segment Solid Rocket Boosters
Powered byoff
Maximum thrust16,000 kN (3,600,000 lbf)
Total thrust32,000 kN (7,200,000 lbf)
Specific impulse269 seconds (2.64 km/s) (vacuum)[citation needed]
Burn time126 seconds
PropellantPBAN, APCP
First stage (Block 1, 1B, 2) – Core Stage
Height64.6 m (211 ft 11 in)
Diameter8.4 m (27 ft 7 in)
Empty mass85,270 kg (187,990 lb)
Gross mass979,452 kg (2,159,322 lb)
Powered by4 RS-25D/E[8]
Maximum thrust7,440 kN (1,670,000 lbf)
Specific impulse363 seconds (3.56 km/s) (sea level), 452 seconds (4.43 km/s) (vacuum)
PropellantLH2 / LOX
Second stage (Block 1) – ICPS
Height13.7 m (44 ft 11 in)
Diameter5 m (16 ft 5 in)
Empty mass3,490 kg (7,690 lb)
Gross mass30,710 kg (67,700 lb)
Powered by1 RL10B-2
Maximum thrust110.1 kN (24,800 lbf)
Specific impulse462 seconds (4.53 km/s)
Burn time1125 seconds
PropellantLH2 / LOX
Second stage (Block 1B, Block 2) – Exploration Upper Stage
Diameter8.4 m (27 ft 7 in)
Powered by4 RL10
Maximum thrust440 kN (99,000 lbf)
PropellantLH2 / LOX
[edit on Wikidata]

The Space Launch System (SLS) is a US super heavy-lift expendable launch vehicle currently under development. It is the primary launch vehicle of NASA's deep space exploration plans,[9][10] including the planned crewed lunar flights of the Artemis program and a possible follow-on human mission to Mars.[11][12][13]

The initial SLS Block 1 is required by the US Congress to lift a payload of 95 metric tons to low Earth orbit (LEO), and will launch Artemis 1, Artemis 2, and Artemis 3 on a circumlunar trajectory. The later Block 1B is intended to debut the Exploration Upper Stage and launch the notional Artemis 4–8.[14] Block 2 is planned to replace the initial Shuttle-derived boosters with advanced boosters and would have a LEO capability of more than 130 metric tons, again as required by Congress.[15] Block 2 is intended to enable crewed launches to Mars.[13] The SLS will launch the Orion Crew and Service Module and use the ground operations and launch facilities at NASA's Kennedy Space Center, Florida.

Vehicle description

Artist's rendering of SLS Block 1B

The SLS is a Shuttle-Derived Launch Vehicle and will have the ability to tolerate a minimum of 13 tanking cycles due to launch scrubs and other launch delays before launch. The assembled rocket is to be able to remain at the launch pad for a minimum of 180 days and can remain in stacked configuration for at least 200 days.[16]

Core Stage

The Space Launch System's Core Stage will be 8.4 meters (28 ft) in diameter and mount a Main Propulsion System (MPS) incorporating four RS-25 engines.[8][17] The core stage will be structurally similar to the Space Shuttle external tank,[18][19] and initial flights will use modified RS-25D engines left over from the Space Shuttle program.[20] Later flights will switch to a cheaper version of the engine not intended for reuse.[21]

The core stage will be fabricated at the Michoud Assembly Facility[22] and is common across all currently planned evolutions of the SLS to avoid the need for substantial redesigns to meet various payload mandates.[23][24][17][25]

Boosters

SLS Booster test at Orbital ATK/Northrop Grumman's desert facility northwest of Ogden, Utah, March 2015

Block 1 and 1B boosters

Blocks 1 and 1B of the SLS will use two five-segment Solid Rocket Boosters (SRBs) based on the four-segment Space Shuttle Solid Rocket Boosters. Modifications to the five-segment boosters included the addition of a center booster segment, new avionics, and lighter insulation. The five-segment SRBs provide approximately 25% more total impulse than the Shuttle SRB and will not be recovered after use.[26][27]

Block 2 advanced boosters (late 2020s)

The advanced boosters for Block 2[28] were intended to be selected through the Advanced Booster Competition, which was to be held in 2015.[8][29]

Several companies proposed boosters for this competition:

  • Aerojet, in partnership with Teledyne Brown, offered a booster powered by three new AJ1E6 LOX/RP-1 oxidizer-rich staged combustion engines, each producing 4,900 kN (1,100,000 lbf) thrust using a single turbopump to supply dual combustion chambers.[30] On 14 February 2013, Aerojet was awarded a $23.3 million, 30-month contract to build a 2,400 kN (550,000 lbf) main injector and thrust chamber.[31]
  • Alliant Techsystems (ATK) proposed an advanced SRB nicknamed "Dark Knight", which would switch to a lighter composite case, use a more energetic propellant, and reduce the number of segments from five to four.[32]
  • Pratt & Whitney Rocketdyne and Dynetics proposed a liquid-fueled booster named Pyrios.[33]

In 2013, the manager of NASA's SLS advanced development office indicated that all three approaches were viable.[34]

However, the 2015 competition was planned in support of Block 1A. A later study found that the advanced booster would have resulted in unsuitably high acceleration,[35] and NASA cancelled Block 1A and the planned competition in 2014.[36][37] In February 2015, it was reported that SLS is expected to fly with the five-segment SRB until at least the late 2020s, and modifications to Launch Pad 39B, its flame trench, and SLS's Mobile Launcher Platform were being evaluated.[36]

Upper Stage

An RL10 engine, like the one pictured above, will be used as the second stage engine in both the ICPS and EUS upper stages.

ICPS - Block 1

Block 1, scheduled to fly Artemis 1 in June 2020,[7] will use the Interim Cryogenic Propulsion Stage (ICPS), a modified Delta IV 5–meter Delta Cryogenic Second Stage (DCSS) powered by a single RL10B-2.[38] Block 1 will be capable of lifting 95 t to LEO in this configuration if the ICPS is considered part of the payload.[4] Artemis 1 will be launched into an initial 1,800 km by −93 km suborbital trajectory to ensure safe disposal of the core stage. ICPS will then perform an orbital insertion burn at apogee and a subsequent translunar injection burn to send Orion towards the moon.[39]

EUS - Block 1B and 2

The Exploration Upper Stage (EUS) was scheduled to fly initially on Artemis 2. Similar to the S-IVB, the EUS would have completed the SLS ascent phase and then re-ignited to send its payload to destinations beyond low-Earth orbit.[40] It was expected to be used by Block 1B and Block 2, share the core stage diameter of 8.4 meters, and be powered by four RL10 engines.[41]

The Artemis 2 flight may fly earlier than planned. In this case it will launch on the less-capable ICPS.[42]

Payload carrying capacity

See also: Super heavy-lift launch vehicle § Comparison
SLS variant Payload mass to ... (metric tons)
low Earth orbit (LEO) trans-lunar injection (TLI) heliocentric orbit (HCO)
Block 1 95 t[4] 26 t[4]
Block 1B 105 t[43] 37 t[4]
Block 2 130 t[5] 45 t[4]

Development history

Diagram of four versions of the Space Launch System rocket
The planned evolution of the Space Launch System

SLS is to replace the retired Space Shuttle as NASA's flagship vehicle. Following the cancellation of the Constellation program, the NASA Authorization Act of 2010 envisioned a single launch vehicle usable for both crew and cargo. SLS is to have the world's highest ever total thrust at launch,[44][45] but not the world's highest ever payload mass.[46][47][48] However, with modern technology the SLS is arguably the most capable heavy lift vehicle built.[18][49]

Program history

During the joint Senate-NASA presentation in September 2011, it was stated that the SLS program had a projected development cost of $18 billion through 2017, with $10 billion for the SLS rocket, $6 billion for the Orion Multi-Purpose Crew Vehicle and $2 billion for upgrades to the launch pad and other facilities at Kennedy Space Center.[50][51] These costs and schedule were considered optimistic in an independent 2011 cost assessment report by Booz Allen Hamilton for NASA.[52]

An unofficial 2011 NASA document estimated the cost of the program through 2025 to total at least $41bn for four 95 t launches (1 uncrewed, 3 crewed),[2][3] with the 130 t version ready no earlier than 2030.[53]

The Human Exploration Framework Team (HEFT) estimated unit costs for Block 0 at $1.6bn and Block 1 at $1.86bn in 2010.[54] However, since these estimates were made the Block 0 SLS vehicle was dropped in late 2011, and the design was not completed.[55] The Space Review estimated the cost per launch at $5 billion, depending on the rate of launches.[56][57] NASA announced in 2013 that the European Space Agency will build the Orion Service Module.[58]

In September 2012, an SLS deputy project manager stated that $500 million per launch is a reasonable target cost for SLS.[59] By comparison, a Saturn V launch cost roughly $1.23 billion in 2016 dollars.[60][61]

In August 2014, as the SLS program passed its Key Decision Point C review and entered full development, costs from February 2014 until its planned launch in September 2018 were estimated at $7.021 billion.[62] Ground systems modifications and construction would require an additional $1.8 billion over the same time period.[63]

In October 2018, NASA's inspector general reported that the Boeing core stage contract had made up 40 percent of the $11.9 billion spent on SLS as of August 2018. By 2021, core stages were expected to have cost a total of US$8.9 billion, which is twice the initial planned amount.[64]

In December 2018, NASA estimated that yearly budgets for SLS will range from US$2.1 to US$2.3B between 2019 to 2023.[65]

In March 2019, the Trump Administration released its Fiscal Year 2020 Budget Request for NASA. This budget did not include any money for the Block 1B and Block 2 variants of SLS. It is uncertain whether these future variants of SLS will be developed.[66] Several launches previously planned for the SLS Block 1B are now expected to fly on commercial launcher vehicles such as Falcon Heavy, New Glenn, Omega, and Vulcan.[67] However, the request for a budget increase of 1.6 billion dollars towards SLS, Orion, and crewed landers along with the launch manifest seem to indicate support of the development of Block 1B, debuting Artemis 3. The Block 1B will be used mainly for co manifested crew transfers and logistic rather than constructing the Gateway. An uncrewed Block 1B is planned to launch the Lunar Surface Asset in 2028, the first lunar outpost of the Artemis program. Block 2 development will most likely start in the late 2020s, after NASA is regularly visiting the lunar surface and shifts focus towards Mars.[68]

Funding history

For fiscal years 2011 through 2018, the SLS program had expended funding totaling $13,999 million in nominal dollars. This is equivalent to $15,109 million adjusting to 2018 dollars using the NASA New Start Inflation Indices.[69]

Fiscal Year Funding ($millions) Status
2011 $1,536.1 Actual[70]
(Formal SLS Program reporting excludes the Fiscal 2011 budget.)[71]
2012 $1,497.5 Actual[72]
2013 $1,414.9 Actual[73]
2014 $1,600.0 Actual[74]
2015 $1,678.6 Actual[75]
2016 $1,971.9 Enacted[75]
2017 $2,150.0 Appropriated[76]
2018 $2,150.0 Appropriated[77]
2011–2018 Total: $13,999M

Excluded from the prior SLS costs are:

  • Costs of the predecessor Ares V / Cargo Launch Vehicle (funded from 2008 to 2010)[78]
  • Costs for the Ares 1 / Crew Launch Vehicle (funded from 2006 to 2010, a total of $4.8 billion[78][79] in development that included the 5-segment Solid Rocket Boosters that will be used on the SLS)
  • Costs to assemble, integrate, prepare and launch the SLS and its payloads such as Orion (funded under the NASA Ground Operations Project,[80] currently about $400M[74] per year)
  • Costs of payloads for the SLS (such as Orion)

Included in the prior SLS costs are:

  • Costs of the interim Upper Stage for the SLS, the Interim Cryogenic Propulsion Stage (ICPS) for SLS, which includes a $412M contract[81]
  • Costs of the final Upper Stage for the SLS, the Exploration Upper Stage (EUS) (funded at $85M in 2016,[82] $300M in 2017[83] and $300M in 2018[84])

There are no current NASA estimates for the average costs per flight of SLS, nor for the SLS program recurring yearly costs once operational. In 2016, the projected annual cost for Orion, SLS, and ground systems was $2 billion or less.[85] NASA associate administrator William H. Gerstenmaier has said that per flight cost estimates will not be provided by NASA.[86]

Constellation

From 2009 to 2011, three full-duration static fire tests of five-segment SRBs were conducted under the Constellation Program, including tests at low and high core temperatures to validate performance at extreme temperatures.[87][88][89]

Early SLS

During the early development of the SLS a number of configurations were considered, including a Block 0 variant with three main engines,[17] a Block 1A variant with upgraded boosters instead of the improved second stage,[17] and a Block 2 with five main engines and the Earth Departure Stage, with up to three J-2X engines.[25] In February 2015, it was determined that these concepts would exceed the congressionally mandated Block 1 and Block 1B baseline payloads.[36]

On 14 September 2011, NASA announced the new launch system,[90] which is intended to take the agency's astronauts farther into space than ever before and provide the cornerstone for future US human space exploration efforts in combination with the Orion spacecraft[91][92][93]

On 31 July 2013, the SLS passed the Preliminary Design Review (PDR). The review included not only the rocket and boosters but also ground support and logistical arrangements.[94] On August 7, 2014 the SLS Block 1 passed a milestone known as Key Decision Point C and entered full-scale development, with an estimated launch date of November 2018.[95][62]

In 2013, NASA and Boeing analyzed the performance of several EUS engine options. The analysis was based on a second stage usable propellant load of 105 metric tons, and compared stages with four RL10 engines, two RL60 engines, or one J-2X engine.[96]

In 2014, NASA also considered using the European Vinci instead of the RL10. The Vinci offers the same specific impulse but with 64% greater thrust, which would allow for the same performance at lower cost.[97][98]

Northrop Grumman Innovation Systems has completed full-duration static fire tests of the five-segment SRBs. Qualification Motor 1 (QM-1) was tested on March 10, 2015.[99] Qualification Motor 2 (QM-2) was successfully tested on June 28, 2016.

Current SLS

Currently three SLS versions are planned: Block 1, Block 1B, and Block 2. Each will use the same core stage with four main engines, but Block 1B will feature the Exploration Upper Stage (EUS), and Block 2 will combine the EUS with upgraded boosters.[43][15][100]

In mid-November 2014, construction of the first core stage hardware began using a new welding system in the South Vertical Assembly Building at NASA's Michoud Assembly Facility.[101] Between 2015 and 2017 NASA test fired RS-25 engines in preparation for use on SLS.[21]

As of late 2015, the SLS program was stated to have a 70% confidence level for the first crewed Orion flight by 2023.[102][103][104]

Confidence article builds for the core stage began on January 5, 2016 and were expected to be completed in late January of that year. Once completed the test articles will be sent to ensure structural integrity at Marshall Spaceflight Center. A structural test article of the ICPS was delivered in 2015, with the stage for Artemis 1 was slated for assembly in late January 2016.[105][needs update]

The first flight of SLS has slipped multiple times, first to 2019,[106] then to June 2020.[7]

The first hold down test will happen second quarter in 2020, which means that its first launch can not happen before 2021. [107]

Criticism

The main criticisms of SLS are program cost, lack of commercial involvement, and the non-competitive nature of a vehicle that is legislated to use Space Transportation System components.

In 2009, the Augustine commission proposed a commercial 75-metric-ton (165,000 lb) launcher with lower operating costs, and noted that a 40–60 t (88,000–132,000 lb) launcher was the minimum required to support lunar exploration.[108]

In 2011–2012, the Space Access Society, Space Frontier Foundation and The Planetary Society called for cancellation of the project, arguing that SLS will consume the funds for other projects from the NASA budget.[109][110][111] U.S. Representative Dana Rohrabacher and others proposed that an orbital propellant depot should be developed and the Commercial Crew Development program accelerated instead.[109][112][113][114][115] A NASA study that was not publicly released[116][117] and another from the Georgia Institute of Technology that was show this option to be possibly cheaper.[118][119] In 2012, the United Launch Alliance also suggested using existing rockets with on-orbit assembly and propellant depots as needed. The lack of competition in the SLS design was highlighted.[120][121][122][123][124]

In 2011, Mars Society/Mars Direct founder Robert Zubrin suggested that a heavy lift vehicle could be developed for $5 billion on fixed-price requests for proposal.[125]

In 2010, SpaceX's CEO Elon Musk claimed that his company could build a launch vehicle in the 140–150 t payload range for $2.5 billion, or $300 million (in 2010 dollars) per launch, not including a potential upper-stage upgrade.[126][127] In the early 2010s, SpaceX went on to start development of BFR, a planned fully reusable super-heavy launch system. Reusability is claimed to allow the lowest cost super-heavy launcher ever made.[128] If the price per launch and payload capabilities for the BFR are anywhere near Musk's claimed capabilities, the rocket will be substantially cheaper than the SLS.[129]

In 2011, Rep. Tom McClintock and other groups called on the Government Accountability Office (GAO) to investigate possible violations of the Competition in Contracting Act (CICA), arguing that Congressional mandates forcing NASA to use Space Shuttle components for SLS are de facto non-competitive, single source requirements assuring contracts to existing shuttle suppliers.[110][130][131] Opponents of the heavy launch vehicle have critically used the name "Senate launch system".[38] The Competitive Space Task Force, in September 2011, said that the new government launcher directly violates NASA's charter, the Space Act, and the 1998 Commercial Space Act requirements for NASA to pursue the "fullest possible engagement of commercial providers" and to "seek and encourage, to the maximum extent possible, the fullest commercial use of space".[109]

In 2013, Chris Kraft, the NASA mission control leader from the Apollo era, expressed his criticism of the system as well.[132] Lori Garver, former NASA Deputy Administrator, has called for cancelling the program.[133] Phil Plait has voiced his criticism of SLS in light of ongoing budget tradeoffs between Commercial Crew Development and SLS budget, also referring to earlier critique by Garver.[134]

In 2015, The Planetary Society claimed that a Mars mission could be conducted within existing budgets.[135]

In 2019, the Government Accountability Office found that NASA had awarded Boeing over $200 million for service with ratings of good to excellent despite cost overruns and delays. The first SLS launch is now expected in 2020 or 2021.[136][137]

Proposed SLS flights

Main article: Proposed SLS and Orion missions

The list below includes NASA planned missions as of May 2019.

Planned SLS missions
Name SLS
Block 		Crew
size 		Launch
date 		Status Duration Destination Purpose
Artemis 1 1 — TBD[138] Planned 25.5 days[139] Distant retrograde lunar orbit Uncrewed lunar orbital test flight of Orion.[140]
Artemis 2 1 4 June 2022[141] Planned 9 days[142] Lunar flyby Crewed free-return cislunar test flight of Orion.[143]
Europa Clipper 1 Cargo — 2023[144] Planned 6 years Jovian orbit Flagship robotic orbiter to explore Europa[145][146]
Artemis 3 1B[147] 4 2024[144] Planned 30 days[144] L2 Southern Near Rectilinear Halo Orbit (NRHO) Crewed flight to the Lunar Orbital Platform-Gateway and landing at the South Pole–Aitken basin.[83]
Artemis 4 1B 4 2025[13] Proposed 26–42 days[141] L2 Southern NRHO Crewed flight to the Gateway to deliver the U.S. Habitation module; lunar landing to test ISRU and Nuclear surface power.[84]
Artemis 5 1B 4 2026[13] Proposed 26–42 days[141] L2 Southern NRHO Crewed flight to the Gateway to deliver a logistics module; first lunar landing with reusable ascent and transfer stages and further ISRU tests.[84]
Artemis 6 1B 4 2027 Proposed 26–42 days[141] L2 Southern NRHO Crewed flight to the Gateway to deliver a logistics module and Canadarm-3; second landing with reusable lander and deployment of Lunar Surface Assets.[84]
Artemis 7 1B Cargo — 2028 Proposed L2 Southern NRHO Uncrewed lunar landing of the Lunar Surface Asset.[84]
Artemis 8 1B 4 2028 Proposed 191–221 days L2 Southern NRHO Crewed flight to the Gateway to deliver a logistics module; extended surface mission at the Lunar Surface Asset.[84]
  • RS-25D engine testing at Stennis Space Center
    RS-25D engine testing at Stennis Space Center
  • SLS core stage segment at Michoud Assembly Facility
    SLS core stage segment at Michoud Assembly Facility
  • SLS Mobile Launcher
    SLS Mobile Launcher
  • SRB segment
    SRB segment
  • SLS vehicle adapter
    SLS vehicle adapter
  • SLS Core Stage being assembled
    SLS Core Stage being assembled
  • Orion launch abort motor
    Orion launch abort motor
  • SLS liquid oxygen tank
    SLS liquid oxygen tank
  • SLS ICPS
    SLS ICPS
  • ICPS on the move
    ICPS on the move

See also

References

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