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Atlas V

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This is an old revision of this page, as edited by 147.105.250.100 (talk) at 17:39, 2 March 2016 (clarified mission success as perfect rate). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.

This article is about the rocket. For the boat, see Atlas V (boat).

Template:Launching/Atlas V (Canaveral)Template:Launching/Atlas V (Vandenberg)

Launch of an Atlas V 401 carrying the LRO and LCROSS
FunctionEELV/Medium-heavy launch vehicle
ManufacturerUnited Launch Alliance
Country of originUnited States
Size
Height58.3 meters (191 ft)
Diameter3.81 meters (12.5 ft)
Mass334,500 kilograms (737,400 lb)
Stages2
Capacity
Payload to LEO
Mass9,800–18,810 kilograms (21,610–41,470 lb)
Payload to GTO
Mass4,750–8,900 kilograms (10,470–19,620 lb)
Associated rockets
Derivative workVulcan
Launch history
StatusActive
Launch sitesCape Canaveral SLC-41
Vandenberg SLC-3E
Total launches61
(401: 31, 411: 3, 421: 5, 431: 2)
(501: 6, 521: 2, 531: 3, 541: 3, 551: 6)
Success(es)60
(401: 30, 411: 3, 421: 5, 431: 2)
(501: 6, 521: 2, 531: 3, 541: 3, 551: 6)
Partial failure(s)1 (401)[1]
First flight401: 21 August 2002
411: 20 April 2006
421: 10 October 2007
431: 11 March 2005
501: 22 April 2010
521: 17 July 2003
531: 14 August 2010
541: 26 November 2011
551: 19 January 2006
Type of passengers/cargoMars Reconnaissance Orbiter
New Horizons
LRO/LCROSS
Solar Dynamics Observatory
Boeing X-37B
Juno
Mars Science Laboratory
Boosters – AJ-60A[2]
No. boosters0 to 5
Height17.0 m (669 in)[2]
Diameter1.6 m (62 in)[2]
Gross mass46,697 kg (102,949 lb)
Maximum thrust1,688.4 kN (379,600 lbf)
Specific impulse279.3 seconds (2.739 km/s)
Burn time94 seconds
PropellantHTPB
Boosters (Heavy, cancelled) – Atlas CCB
No. boosters2
Height32.46 m (106.5 ft)
Diameter3.81 m (12.5 ft)
Empty mass23,648 kg (52,135 lb)
Propellant mass286,795 kg (632,275 lb)
Powered by1 RD-180
Maximum thrust3,827 kN (860,000 lbf) (SL)
4,152 kN (933,000 lbf) (Vac)
Specific impulse311.3 seconds (3.053 km/s) (SL)
337.8 seconds (3.313 km/s) (Vac)
Burn time253 seconds
PropellantRP-1/LOX
First stage – Atlas CCB
Height32.46 m (106.5 ft)
Diameter3.81 m (12.5 ft)
Empty mass21,054 kg (46,416 lb)
Propellant mass284,089 kg (626,309 lb)
Powered by1 RD-180
Maximum thrust3,827 kN (860,000 lbf) (SL)
4,152 kN (933,000 lbf) (Vac)
Specific impulse311.3 seconds (3.053 km/s) (SL)
337.8 seconds (3.313 km/s) (Vac)
Burn time253 seconds
PropellantRP-1/LOX
Second stage – Centaur
Height12.68 m (41.6 ft)
Diameter3.05 m (10.0 ft)
Empty mass2,316 kg (5,106 lb)
Propellant mass20,830 kg (45,920 lb)
Powered by1 RL10A or 1 RL10C
Maximum thrust99.2 kN (22,300 lbf) (RL10A)
Specific impulse450.5 seconds (4.418 km/s) (RL10A-4-2)
Burn time842 seconds (RL10A-4-2)
PropellantLH2/LOX
[edit on Wikidata]

Atlas V is an active expendable launch system in the Atlas rocket family. Atlas V was formerly operated by Lockheed Martin, and is now operated by the Lockheed Martin-Boeing joint venture United Launch Alliance. Each Atlas V rocket uses a Russian-built RD-180 engine burning kerosene and liquid oxygen to power its first stage and an American-built RL10 engine burning liquid hydrogen and liquid oxygen to power its Centaur upper stage. The RD-180 engines are provided by RD AMROSS, while Aerojet Rocketdyne provides both the RL10 engines and the strap-on boosters used in some configurations. The standard payload fairing sizes are 4 or 5 meters in diameter and of various lengths, and are made by RUAG Space. Fairings sizes as large as 7.2 m in diameter and up to 32.3 m in length have been considered.[3] The rocket is assembled in Decatur, Alabama and Harlingen, Texas.

In its more than six dozen launches, starting with its maiden launch in August 2002, Atlas V has had a perfect mission success rate. One flight on June 15, 2007, NRO L-30, experienced an upper-stage anomaly when the engine in the vehicle's Centaur upper stage shut down four seconds early, leaving the payload—a pair of naval signals intelligence satellites—in a lower than intended orbit. However, the customer, the National Reconnaissance Office, categorized the mission as a success.[4][5]

History

The Atlas V is the newest member of the Atlas family. Compared to the Atlas III vehicle, there are numerous changes. Compared to the Atlas II, it is a near-redesign. There was no Atlas IV.

  1. The "1.5 staging" technique was dropped on the Atlas III, although the same RD-180 engine is used.[6] The RD-180 features a dual-combustion chamber, dual-nozzle design and is fueled by a kerosene/liquid oxygen mixture.
  2. The main-stage diameter increased from 10 feet to 12.5 feet. As with the Atlas III, the different mixture ratio of the engine called for a larger oxygen tank (relative to the fuel tank) compared to Western engines and stages.[citation needed]
  3. The first stage tanks no longer use stainless steel monocoque "balloon" construction. The tanks are isogrid aluminum and are structurally stable when unpressurized.[6]
  4. Use of aluminum, with a higher thermal conductivity than stainless steel, requires insulation for the liquid oxygen. The tanks are covered in a polyurethane-based layer. [citation needed]
  5. Accommodation points for parallel stages, both smaller solids and identical liquids, are built into first stage structures.[6]

The Atlas V was developed by Lockheed Martin Commercial Launch Services as part of the US Air Force Evolved Expendable Launch Vehicle (EELV) program and made its inaugural flight on August 21, 2002. The vehicle operates out of Space Launch Complex 41 at Cape Canaveral Air Force Station and Space Launch Complex 3-E at Vandenberg Air Force Base. Lockheed Martin Commercial Launch Services continues to market the Atlas V to commercial customers worldwide.[7]

The Atlas V first stage, the Common Core Booster (CCB), is 12.5 ft (3.8 m) in diameter and 106.6 ft (32.5 m) in length. It is powered by a single Russian RD-180 main engine burning 627,105 lb (284,450 kg) of liquid oxygen and RP-1. The booster operates for about four minutes, providing about 4 meganewtons (860,000 lbf) of thrust.[6] Thrust can be augmented with up to five Aerojet strap-on solid rocket boosters, each providing an additional 1.27 meganewtons (285,500 lbf) of thrust for 94 seconds.

The Centaur upper stage uses a pressure stabilized propellant tank design and cryogenic propellants. The Centaur stage for Atlas V is stretched 5.5 ft (1.68 m) relative to the Atlas IIAS Centaur and is powered by either one or two Aerojet Rocketdyne RL10A-4-2 engines, each engine developing a thrust of 99.2 kN (22,300 lbf). The inertial navigation unit (INU) located on the Centaur provides guidance and navigation for both the Atlas and Centaur, and controls both Atlas and Centaur tank pressures and propellant use. The Centaur engines are capable of multiple in-space starts, making possible insertion into low Earth parking orbit, followed by a coast period and then insertion into GTO. A subsequent third burn following a multi-hour coast can permit direct injection of payloads into geostationary orbit.[8] As of 2006, the Centaur vehicle had the highest proportion of burnable propellant relative to total mass of any modern hydrogen upper stage and hence can deliver substantial payloads to a high energy state.[9]

Many systems on the Atlas V have been the subject of upgrade and enhancement both prior to the first Atlas V flight and since that time. Work on a new Fault Tolerant Inertial Navigation Unit (FTINU) started in 2001 to enhance mission reliability for Atlas vehicles by replacing the existing non-redundant navigation and computing equipment with a fault tolerant unit.[10][full citation needed] The upgraded FTINU first flew in 2006,[11][full citation needed] and in 2010 a follow-on order for more FTINU units was awarded.[12][full citation needed]

On December 5, 2015, Atlas V lifted its heaviest payload to date into orbit—a 16,517-pound (7,492 kg) - Cygnus resupply craft.[13]

2007 valve anomaly

The only anomalous event in the use of the Atlas V launch system occurred on June 15, 2007, when the engine in the Centaur upper stage of an Atlas V shut down early, leaving its payload – a pair of NRO L-30 ocean surveillance satellites – in a lower than intended orbit. The cause of the anomaly was traced to a leaky valve, which allowed fuel to leak during the coast between the first and second burns. The resulting lack of fuel caused the second burn to terminate 4 seconds early.[14] Replacing the valve led to a delay in the next Atlas V launch.[15]

Proposed development options

Atlas V CTS (Crew Transportation System)

From 2006 through at least 2014 ULA made proposals and did some amount of design work for a human-rated version of the Atlas V. Atlas V was selected by NASA in late 2014, in conjunction with the Boeing CST-100 space capsule, to be used for human flight as early as 2017.

The work began as early as 2006, by ULA's predecessor company Lockheed Martin. An agreement between Lockheed and Bigelow Aerospace that year was reported that could lead to commercial private trips to low Earth orbit 7.(LEO).[16]

Beginning in 2010, ULA did design and simulation work to human-rate the Atlas V for carrying passengers. ULA won a 2010 small contract of US$6,700,000 in the first phase of the NASA Commercial Crew Development Program (CCDev) to develop an Emergency Detection System (EDS) for human-rating the Atlas V launch vehicle.[17] As of February 2011, ULA "is still finishing up work on its $6.7-million award... In December ULA carried out a demonstration of its Emergency Detection System ... The company said it received an extension from NASA until April 2011 'to enable us to finish critical timing analyses tasks' for [the] fault coverage analysis work."[18]

NASA solicited proposals for CCDev phase 2 in October 2010, under which ULA made a proposal for funding to "finish designing a key safety system for potential commercial crew launches on its Atlas and Delta rocket fleet." While NASA's goal then was to get astronauts to orbit by 2015, ULA President and CEO Michael Gass stated "I think we need to stretch our goals to have commercial crew service operating by 2014" and committed ULA to meet that schedule if funded.[19] Other than the addition of the Emergency Detection System, no major changes were expected to the Atlas V rocket, but ground infrastructure modifications were planned. The most likely candidate for the human-rating was the 402 configuration, with dual RL10 engines on the Centaur upper stage and no solid rocket boosters.[19]

On July 18, 2011 NASA and ULA announced an agreement on the possibility of certifying the Atlas V to NASA's "human-rating" standards.[20] ULA agreed to provide NASA with data on the Atlas V, while NASA would provide ULA with draft human certification requirements.[20] As of July 2011 Bigelow Aerospace was still considering the use of a human-rated Atlas V for carrying spaceflight participants to its private space station.[21]

In 2011, Sierra Nevada Corporation (SNC) picked the Atlas V to be the booster for its still-under-development Dream Chaser crewed spacecraft.[22] The Dream Chaser is designed to be a crewed vertical-takeoff, horizontal-landing (VTHL) lifting-body spaceplane that will be placed into LEO by an Atlas V, and is a proposed CCDev ISS crew transport vehicle.[22] However, in late 2014 NASA did not select the Dream Chaser to be one of the two vehicles selected under the Commercial Crew competition.

On August 4, 2011 Boeing announced it would use the Atlas V as the initial launch vehicle for its CST-100 crewed spaceship, intended for both NASA-funded trips to the International Space Station, as well as for private trips to the proposed Bigelow Commercial Space Station.[23][24] As of August 2011, a three-flight test program had been projected to be completed by 2015, and potentially certify the Atlas V/CST-100 combination for human-spaceflight operations.[24] The first flight was expected to include an Atlas V rocket integrated with an unpiloted CST-100 capsule, to launch from Cape Canaveral's LC-41 in early 2015 into LEO,[23] with the second flight hoped to be an in-flight launch abort system demonstration in the middle of that year,[24] and the test-flight phase expected to culminate with a crewed mission at the end of 2015, carrying two Boeing test-pilot astronauts into LEO and returning them safely.[24] In August 2012, George Sowers, ULA's vice president for Human Launch Services, stated that if funded, the first manned flight of the Atlas V could occur by late 2015.[25] As of 2015, delays in the program had resulted in the two orbital demonstration missions being pushed back to mid-2017.[26]

Replacement for the RD-180 engine

Geopolitical and US political considerations in 2014 led to an effort by ULA to consider the possible replacement of the Russian-supplied RD-180 engine used on the first stage booster of the Atlas V. Formal study contracts were issued in June 2014 to a number of US rocket engine suppliers.[27] The results of those studies have led to decisions by ULA to develop a new launch vehicle to replace the Atlas V and Delta IV existing fleet.

The Aerojet AR-1 rocket engine under development as of 2015, is a backup plan to the successor rocket Vulcan, to re-engine the Atlas V.[28] In addition to the ULA backup plan, a consortium of companies including Aerojet and Dynetics seek license production or rights to the Atlas V to manufacture it using the AR-1 engine in place of the RD-180. This proposal has been declined by ULA.[29]

New Solid Boosters

In 2015, ULA announced that the Aerojet Rocketdyne-produced AJ-60A SRBs currently in use on Atlas V will be phased out in favor of new GEM 63 boosters produced by Orbital ATK. A stretched version of this booster will be used on the upcoming Vulcan rocket.[30]

Successor: Vulcan

The Vulcan rocket is the intended replacement for all three of ULA's currently flying rockets, the Atlas V, Delta II, and Delta IV.[31]

In September 2014, ULA announced that it has entered into a partnership with Blue Origin to develop the BE-4 LOX/methane engine to replace the RD-180 on a new first stage booster. As the Atlas V core is designed around RP-1 fuel and cannot be retrofitted to use a methane-fueled engine, a new first stage must be developed. This booster will be derived from the first stage tankage of the Delta IV, using two of the 2,400-kilonewton (550,000 lbf)-thrust BE-4 engines.[27][32][33] The engine is already in its third year of development by Blue Origin, and ULA expects the new stage and engine to start flying no earlier than 2019.

Vulcan will initially use the same Centaur upper stage as on Atlas V, later to be upgraded to ACES.[32] It will also use a variable number of optional solid rocket boosters, called the GEM 60XL, derived from the new solid boosters planned for Atlas V.[30]

Atlas V HLV

In 2006, ULA offered an Atlas V HLV (Heavy Lift Vehicle) option that would use three Common Core Booster (CCB) stages strapped together to lift a 29,400 kg payload to low Earth orbit.[34] ULA stated at the time that 95% of the hardware required for the Atlas HLV has already been flown on the Atlas V single core vehicles.[3] The lifting capability of the proposed rocket was to be roughly equivalent to the Delta IV Heavy,[3] which utilizes RS-68 engines developed and produced domestically by Aerojet Rocketdyne.

A 2006 report, prepared by the RAND Corporation for the Office of the Secretary of Defense, stated that Lockheed Martin had decided not to develop an Atlas V heavy-lift vehicle (HLV).[35] The report recommended for the Air Force and the National Reconnaissance Office to "determine the necessity of an EELV heavy-lift variant, including development of an Atlas V Heavy", and to "resolve the RD-180 issue, including coproduction, Stockpile, or U.S. development of an RD-180 replacement."[36]

As of March 2010, ULA stated that the Atlas V HLV configuration could be available to customers 30 months from the date of order.[3]

In March 2015, United Launch Alliance CEO Tory Bruno confirmed on Twitter that the Atlas V HLV will not be developed, instead they would be focusing on the Next Gen Launch System (Vulcan).

Atlas Phase 2

With the merger of Boeing and Lockheed Martin space operations into United Launch Alliance in the mid-2000s, the Atlas V program became able to share the tooling and processes for 5-meter-diameter stages used on Delta IV. This led to a concept being put forth to combine Delta IV production processes into a new Atlas design: the "Atlas Phase 2". If the first stage were to be 5 meters in diameter, such a stage could accept dual RD-180 engines. The conceptual heavy-lift vehicle was known as Atlas Phase 2 or "PH2".

An Atlas V PH2-Heavy (three 5 m stages in parallel; six RD-180s) along with Shuttle-derived, Ares V and Ares V Lite, was considered as a theoretically-possible heavy lifter for use in future space missions in the Augustine Report.[37] If built, the Atlas PH2 HLV was projected to be able to launch a payload mass of approximately 70 metric tons into an orbit of 28.5 degree-inclination.[37] None of the Atlas V Phase 2 proposals reached development.

GX rocket

Main article: GX (rocket)

The Atlas V Common Core Booster was to have been used as the first stage of the joint US-Japanese GX rocket, which was scheduled to make its maiden flight in 2012.[38] GX launches would have been from the Atlas V launch complex at Vandenberg AFB, SLC-3E.

In December 2009, the Japanese government decided to cancel the GX project.[39]

Cost

In 2013, the cost for an Atlas V 541 launch to GTO (including launch services, payload processing, launch vehicle integration mission, unique launch site ground support and tracking, data and telemetry services) was about $223 million.[40] In 2014 the NASA contracted ULA to launch the Solar Orbiter for around $173 million.[41] In 2015, ULA stated that a low-end Atlas V sells for about $164 million.[42]

Since around 2005, Atlas V has not been cost-competitive for most commercial launches, where launch costs were about $100 million per satellite to GTO in 2013.[43]

Variants

An Atlas V 551 with the New Horizons probe launches from Launch Pad 41 in Cape Canaveral

Each Atlas V booster configuration has a three-digit designation that indicates the features of that configuration. The first digit shows the diameter (in meters) of the payload fairing, and always has a value of "4" or "5". The second digit indicates the number of solid rocket boosters attached to the base of the rocket, and can range from "0" through "3" with the 4-meter fairing, and "0" through "5" with the 5-meter fairing. The third digit represents the number of engines on the Centaur stage, either "1" or "2". For example, an Atlas V 552 has a 5-meter fairing, five solid rocket boosters, and two Centaur engines, whereas an Atlas V 431 has a 4-meter fairing, three solid rocket boosters, and a single Centaur engine.[44] As of 2014, only the single-engine Centaur (SEC) has been used, with the first launch using the dual-engine Centaur (DEC) upper stage planned for November 2016, when an Atlas V 402 will carry the Sierra Nevada Dream Chaser vehicle for its first orbital test flight.[45]

The 4-meter fairing, originally designed for the Atlas II booster, comes in three different lengths, the original 9-meter high version, as well as fairings 10 meters (first flown on the AV-008/Astra 1KR launch) and 11 meters (seen on the AV-004/Inmarsat-4 F1 launch) high. Lockheed Martin had the 5.4-meter (4.57 meters usable) payload fairing for the Atlas V developed and built by RUAG Space (former Oerlikon Space[46][full citation needed]) in Switzerland.[failed verification] The RUAG fairing uses carbon fiber composite construction, based on flight-proven hardware from the Ariane 5. Three configurations will be manufactured to support the Atlas V. The short (10-meter long) and medium (13-meter long) configurations will be used on the Atlas V 500 series. The 16-meter long configuration would be used on the Atlas V Heavy. The classic fairing covers only the payload, leaving the Centaur stage exposed to open air. The RUAG fairing encloses the Centaur stage as well as the payload.[47]

Versions

As of June 2015, all versions of the Atlas V, its design and production rights, and intellectual property rights are owned by ULA and Lockheed Martin.[48]

List Date: February 5, 2016[49] Mass to LEO numbers are at an inclination of 28.5 degrees.

Version Fairing CCBs SRBs Upper stage Payload to LEO Payload to GTO Launches to date
401 4 m 1 – SEC 9,797 kg[50] 4,750 kg[50] 31
402 4 m 1 – DEC 12,500 kg[51] – 0
411 4 m 1 1 SEC 12,150 kg[50] 5,950 kg[50] 3
412 4 m 1 1 DEC – – 0
421 4 m 1 2 SEC 14,067 kg[50] 6,890 kg[50] 5
422 4 m 1 2 DEC - - 0
431 4 m 1 3 SEC 15,718 kg[50] 7,700 kg[50] 2
501 5.4 m 1 – SEC 8,123 kg[50] 3,775 kg[50] 6
502 5.4 m 1 – DEC – – 0
511 5.4 m 1 1 SEC 10,986 kg[50] 5,250 kg[50] 0
512 5.4 m 1 1 DEC – – 0
521 5.4 m 1 2 SEC 13,490 kg[50] 6,475 kg[50] 2
522 5.4 m 1 2 DEC – – 0
531 5.4 m 1 3 SEC 15,575 kg[50] 7,475 kg[50] 3
532 5.4 m 1 3 DEC – – 0
541 5.4 m 1 4 SEC 17,443 kg[50] 8,290 kg[50] 3
542 5.4 m 1 4 DEC – – 0
551 5.4 m 1 5 SEC 18,814 kg[50] 8,900 kg[50] 6
552 5.4 m 1 5 DEC 20,520 kg[51] – 0
Heavy (HLV/5H1) 5.4 m 3 – SEC – – 0
Heavy (HLV DEC/5H2) 5.4 m 3 – DEC 29,400 kg[50] – 0

Atlas V launches

Template:Details3

List Date: February 5, 2016

For planned launches, see:
List of Atlas launches (2010–2019)
  • Core stage of an Atlas V being raised to a vertical position
    Core stage of an Atlas V being raised to a vertical position
  • X-37B OTV-1 (Orbital Test Vehicle) being encased in its payload fairing for its April 22, 2010 launch.
    X-37B OTV-1 (Orbital Test Vehicle) being encased in its payload fairing for its April 22, 2010 launch.
  • An Atlas V 541 is moved to the launch pad
    An Atlas V 541 is moved to the launch pad
  • Atlas V 401 on launch pad
    Atlas V 401 on launch pad
  • Atlas V ignition
    Atlas V ignition

See also

Wikinews has related news:

Comparable rockets:

References

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