|Atlas II, III and V comparison|
|Role||Expendable launch system with various applications|
United Launch Alliance
|First flight||17 December 1957|
|Status||Atlas V (current)|
|Primary users||United States Air Force|
National Aeronautics and Space Administration
Atlas is a family of US missiles and space launch vehicles that originated with the SM-65 Atlas. The Atlas intercontinental ballistic missile (ICBM) program was initiated in the late 1950s under the Convair Division of General Dynamics. Atlas was a liquid propellant rocket burning RP-1 fuel with liquid oxygen in three engines configured in an unusual "stage-and-a-half" or "parallel staging" design: two outboard booster engines were jettisoned along with supporting structures during ascent, while the center sustainer engine, propellant tanks and other structural elements remained connected through propellant depletion and engine shutdown.
The Atlas name was originally proposed by Karel Bossart and his design team working at Convair on project MX-1593. Using the name of a mighty titan from Greek mythology reflected the missile's place as the biggest and most powerful at the time. It also reflected the parent company of Convair, the Atlas Corporation.
The missiles saw only brief ICBM service, and the last squadron was taken off operational alert in 1965. However, from 1962 to 1963 Atlas boosters launched the first four US astronauts to orbit the Earth (in contrast to the preceding two Redstone suborbital launches). The Atlas-Agena and Atlas-Centaur satellite launch vehicles were also derived directly from the original Atlas. The Atlas-Centaur was evolved into the Atlas II, various models of which were launched 63 times between 1991 and 2004. There were only six launches of the succeeding Atlas III, all between 2000 and 2005. The Atlas V is still in service, with launches planned into the 2020s.
The Atlas was used as the expendable launch system with both the Agena and Centaur upper stages for the Mariner space probes used to explore Mercury, Venus, and Mars (1962–1973); and to launch ten of the Mercury program missions (1962–1963).
The first successful test launch of an SM-65 Atlas missile was on 17 December 1957. Approximately 350 Atlas missiles were built.
The Atlas boosters would collapse under their own weight if not kept pressurized with nitrogen gas in the tanks when devoid of propellants. The Atlas booster was unusual in its use of "balloon" tanks. The rockets were made from very thin stainless steel that offered minimal or no rigid support. It was pressure in the tanks that gave the rigidity required for space flight. In order to save weight they were not painted and needed a specially designed oil to prevent rust. This was the original use of WD-40 water displacement oil.
The SM-65 Atlas was used as a first stage for satellite launch vehicles for half a century. Many were eventually converted to orbital launch vehicles after they were removed from service as missiles. Missiles converted into Atlas E/F "space boosters" were used to launch the early "Block I" GPS satellites.
Early Atlas rockets were also built specifically for non-military uses. On 18 December 1958, an Atlas was used to launch the Signal Communication by Orbiting Relay Equipment (SCORE) satellite, which was "the first prototype of a communications satellite, and the first test of any satellite for direct practical applications." The communications payload was placed into low Earth orbit on Atlas serial number 10B without an upper stage. Atlas 10B/SCORE, at 8,750 lb (3,970 kg) was the heaviest artificial object then in orbit, the first voice relay satellite, and the first human-made object in space easily visible to the naked eye due to the large, mirror-polished stainless steel tank. This was the first flight in what would be a long career for the Atlas as a satellite launcher.
Atlas D missile-derived SLV-3s were used for orbital launches with the RM-81 Agena and Centaur upper stages. The modified Atlas LV-3B was used for the orbital element of Project Mercury, launching four crewed Mercury spacecraft into low Earth orbit. Atlas D launches were conducted from Cape Canaveral Air Force Station, at Launch Complexes 11, 12, 13 and 14, and Vandenberg AFB Launch Complex 576.
By 1979, Atlas space launcher variants had been whittled down to just the Atlas-Centaur and some refurbished ICBMs. The launch rate of Atlases decreased in the 1980s due to the advent of the space shuttle, but Atlas launches continued until 2004, when the last "classic" Atlas with balloon tanks and the jettisonable booster section launched a comsat for the Air Force.
Atlas boosters were also used for the last four crewed Project Mercury missions, the first United States crewed space program. On February 20, 1962 it launched Friendship 7, which made three Earth orbits carrying John Glenn, the first United States astronaut to orbit the Earth. Identical Atlas boosters successfully launched three more crewed Mercury orbital missions from 1962 to 1963.
Atlas saw the beginnings of its "workhorse" status during the Mercury-Atlas missions, which resulted in Lt. Col. John H. Glenn Jr. becoming the first American to orbit the Earth in 1962 (Major Yuri A. Gagarin, a Soviet cosmonaut, was the first human in orbit in 1961.) Atlas was also used throughout the mid-1960s to launch the Agena Target Vehicles used during the Gemini program.
Beginning in 1960, the Agena upper-stage, powered by hypergolic propellant, was used extensively on Atlas launch vehicles. The United States Air Force, NRO and CIA used them to launch SIGINT satellites. NASA used them in the Ranger program to obtain the first close-up images of the surface of the Moon and for Mariner 2, the first spacecraft to fly by another planet. Each of the Agena target vehicles used for the later space rendezvous practice missions of Gemini was launched on an Atlas rocket.
The Atlas-Centaur was an expendable launch system derived from the SM-65D Atlas missile. Launches were conducted from two pads of the Launch Complex 36 at Cape Canaveral Air Force Station, Florida. The Atlas' engines were upgraded and the structure reinforced for the large upper stage, along with elongated propellant tanks.
An Atlas rocket is shown exploding in the penultimate shot of the 1983 art film Koyaanisqatsi, directed by Godfrey Reggio. The vehicle shown in the movie was the first launch attempt of an Atlas-Centaur in May 1962.
Beginning in 1963, the liquid hydrogen-fueled Centaur upper stage was also used on dozens of Atlas launches. NASA launched the Surveyor program lunar lander spacecraft and most of the Mars-bound Mariner program spacecraft with Atlas-Centaur launch vehicles.
The last Atlas E/F spacecraft launch was conducted on 24 March 1995, using a rocket which had originally been built as an Atlas-E. The last Atlas E/F launch to use a rocket which had originally been built as an Atlas-F was conducted on 23 June 1981.
Atlas E/F was used to launch the Block I series of GPS satellites from 1978 to 1985. The last refurbished Atlas-F vehicle was launched from Vandenberg AFB in 1995 carrying a satellite for the Defense Meteorological Satellite Program.
|Model name||First launch||Last launch||Total launches||Successes||ICBM base||Upper stage||Notable payloads||Remarks|
|Atlas-Vega||-||-||0||0||Atlas E||storable propellant stage||none||Development was essentially identical to Atlas-Agena, and cancelled accordingly in 1959|
|Atlas-Able||1959||1960||3||0||Atlas-D/Able(Delta-A)||Altair||none||2 rockets failed during static firing, and 3 during attempts to launch Pioneer spacecrafts to the Moon|
|Atlas LV-3A||1960||1968||49||38||Atlas D||Agena||Mariner 2, Ranger program, Missile Defense Alarm System||The baseline Atlas-Agena sub-family vehicle|
|Atlas LV-3B||1959||1963||9||9||Atlas D||none||Friendship 7, Aurora 7, Sigma 7, Faith 7||Human-rated Atlas LV-3A|
|Atlas SLV-3||1964||1968||51||46||Atlas D||Agena||Corona, KH-7 Gambit||same as LV-3A except reliability improvements|
|Atlas SLV-3A||1969||1978||10||9||Atlas D||Agena||Canyon||same as SLV-3 except stretched 2.97 m|
|Atlas SLV-3B||1966||1966||1||1||Atlas D||Agena D||Orbiting Astronomical Observatory 1|
|Atlas LV-3C||1963||1967||11||8||Atlas D||Centaur C||?||The baseline Atlas-Centaur sub-family vehicle|
|Atlas SLV-3C||1967||1972||17||14||Atlas D||Centaur D||?||Same as LV-3C stretched 1.3 m|
|Atlas SLV-3D||1973||1983||32||29||Atlas D||Centaur D1A||?||Same as SLV-3C except Centaur uprated and Atlas electronics integrated with Centaur|
|Atlas G||1984||1987||6||4||Atlas G||Centaur D1A||?||Same as SLV-3D but Atlas longer by 2.06 m|
|Atlas I||1990||1997||11||8||Atlas G derived||Centaur D1A derived||CRRES||Same as Atlas G except strengthened for 4.27 m payload fairing and ring laser gyro added.|
|Atlas II||1991||1998||10||10||Atlas G derived||Centaur D1A derived||Eutelsat||Same as Atlas I except Atlas stretched 2.74 m, engines uprated, added hydrazine roll control, fixed foam insulation, deleted verniers, and Centaur stretched 0.9 m. Development done by General Dynamics (now part of Lockheed Martin).|
|Atlas IIA||1992||2002||23||23||Atlas G derived||Centaur D1A derived||-||Same as Atlas II except Centaur RL10 engines uprated to 88 kN of thrust and 6.5 Isp increase from extendible RL10 nozzles|
|Atlas IIAS||1993||2004||30||30||Atlas G derived||Centaur D1A derived||-||Same as Atlas IIA except 4 Castor IVA strap-on boosters added|
|Atlas D-OV1||1965||1967||7||6||Atlas D||none||?||ICBM refurbished for orbital launch|
|Atlas E||1980||1995||23||21||Atlas E||none||?||ICBM refurbished for orbital launch|
|Atlas F||1968||1981||23||22||Atlas F||none||?||ICBM refurbished for orbital launch|
|Atlas H||1983||1987||5||5||Modified Atlas G||Centaur stage removed||?||Atlas G modified for West Coast Avionics
SLC 3E modified for Space Booster hold down system versus weapon system flyaway
The first stage of the Atlas III discontinued the use of three engines and 1.5 staging in favor of a single Russian-built Energomash RD-180 engine, while retaining the stage's balloon tank construction. The Atlas III continued to use the Centaur upper stage, available with single or dual RL10 engines.
The Atlas V, currently in service, was developed by Lockheed Martin as part of the US Air Force Evolved Expendable Launch Vehicle (EELV) program. The first was launched on August 21, 2002. In 2006, operation was transferred to United Launch Alliance (ULA), a joint-venture between Lockheed Martin and Boeing. Lockheed Martin continues to market the Atlas V to commercial customers. Atlas V is built in Decatur, Alabama and maintains two launch sites: Space Launch Complex 41 at Cape Canaveral Air Force Station and Space Launch Complex 3-E at Vandenberg Air Force Base.
The Atlas V's first stage is called the Common Core Booster (CCB), which continues to use the Energomash RD-180 introduced in the Atlas III, but employs a rigid framework instead of balloon tanks. The rigid fuselage is heavier, but easier to handle and transport, eliminating the need for constant internal pressure. Up to five Aerojet Rocketdyne strap-on solid rocket boosters can be used to augment first stage thrust. The upper stage remains the Centaur, powered by a single or dual Aerojet Rocketdyne RL10 engines.
|Model name||First launch||Last launch||Total launches||Successes||1st-stage engines||Upper-stage engines||Notable payloads||Remarks|
|Atlas IIIA||2000||2004||2||2||1xRD-180||1xRL10A||Eutelsat W4||major revision of Atlas IIA, with new RD-180 first-stage engine, normal staging, first stage stretched 4.4 m and strengthened. First single RL10 engine Centaur.|
|Atlas IIIB||2002||2005||4||4||1xRD-180||1xRL10A||Same as Atlas IIIA, except for Centaur stretched 1.7 m and an optional dual engine Centaur.|
|Atlas V 400||2002||-||25||24||1xRD-180||1xRL10A||major revision of Atlas III, with new first-stage structure (CCB) and with optional solid strap-on boosters.|
|Atlas V 500||2003||-||12||12||1xRD-180||1xRL10A||revision of Atlas V 400, with optional solid strap-on boosters, and Centaur stage encapsulated inside 5.4 m payload fairing.|
In 2014, US Congress passed legislation restricting the purchase and use 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.
In September 2014, ULA announced that it had entered into a partnership with Blue Origin to develop the BE-4 LOX/methane engine to replace the RD-180 on the new Vulcan rocket. The engine has been in development for 8 years by Blue Origin, and ULA expects the new stage and engine to start flying no earlier than 2021.
In December 2014, legislation to prevent the award of further military launch contracts to vehicles that use Russian-made engines was approved by the US Congress. The bill allows ULA to continue to use the 29 RD-180 engines already on order at the time.
Prior to the April 2015 announcement of the Vulcan launch vehicle, during the first decade since ULA was formed from Lockheed Martin and Boeing, there were a number of proposals and concept studies of future launch vehicles. None were subsequently funded for full-up development. Two of those concepts were the Atlas V Heavy and the Atlas Phase 2.
The Atlas V Heavy was a ULA concept proposal that would have used three Common Core Booster (CCB) stages strapped together to provide the capability necessary to lift 25 tonne payload to low Earth orbit. ULA stated that approximately 95% of the hardware required for the Atlas HLV had already been flown on the Atlas V single-core vehicles.
A 2006 report, prepared by 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). 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."[needs update]
After December 2006, with the merger of Boeing and Lockheed-Martin space operations into United Launch Alliance, the Atlas V program gained access to the tooling and processes for 5.4 m diameter stages used on Delta IV. A 5.4 m diameter stage could have conceivably accepted dual RD-180 engines. The resulting conceptual heavy-lift vehicle was called "Atlas Phase 2" or "PH2" in the 2009 Augustine Report. An Atlas V PH2-Heavy (three 5 m stages in parallel; six RD-180s) along with Shuttle-derived, Ares V and Ares V Lite, were considered as a possible heavy lifter concept for use in future space missions in the Augustine Report. The Atlas PH2 HLV concept vehicle would have notionally been able to launch a payload mass of approximately 70 metric tons into an orbit of 28.5 degree-inclination. The concept did not proceed onto full development, and was never built.
Review of U.S. Human Spaceflight Plans Committee