Atlas III

Last updated

The second stage of Atlas III was the Centaur. It was powered by one or two Pratt & Whitney (later Aerojet Rocketdyne) RL-10 engines, fueled by liquid hydrogen and liquid oxygen. Compared to the Atlas II, the added thrust and efficiency of the first stage of Atlas III allowed for one RL-10 engine to be removed from Centaur, and Atlas III was the first Atlas to offer a single-engine Centaur. The engines of a dual-engine Centaur were mounted directly on the aft propellant tank bulkhead, whereas the engine on a single-engine Centaur was mounted on a specially-made beam connected to those existing dual-engine mounts. The single-engine Centaur featured an RL-10A-4-1 engine with a 51 cm (20 in) extendible nozzle, which increased the engine's thrust by 1.4 kN and specific impulse by 6.5 seconds. [1]

Centaur hosted the vehicle's avionics and flight computers and controlled the entire flight. The RL-10 engine on the single-engine Centaur featured electromechanical gimballing, as opposed to the hydraulic gimballing on other variants. [1]

The tanks of Centaur were balloon tanks like the first stage, made from stainless steel. PVC foam insulation was installed on the outside of the tank walls to help limit propellant boiloff inside the tanks. [1]

Two variants of Centaur flew on Atlas III:

Flying a mission on an Atlas IIIB with a dual-engine Centaur provided a nearly 400 kg boost in payload capability to geostationary transfer orbit compared to using a single-engine Centaur. [1]

An Extended Mission Kit (EMK) was available for Centaur. This kit included additional helium bottles, radiation shielding on the LOX tank and electronics, and thermal paint to maintain stable temperatures for electronics. [1]

Payload fairing

Two aluminum fairing models (which previously flew on the Atlas II) were available for the Atlas III, both with a 4.2 m (14 ft) diameter: [1] [5]

Fairing selection had a small but noticeable impact on the performance of Atlas III. For example, when going to a 185 km (115 mi) low Earth orbit, flying with the Extended payload fairing would reduce the payload capacity by around 45 kg (99 lb) compared to flying with the Large payload fairing. [1]

Both fairing options were still flown on the Atlas V rocket until 2022. [6] For the Atlas V, these fairings were part of the 400-series of that rocket, and a further extended option ("Extra Extended") was available. [1] [7]

Launches

The first flight of the Atlas III occurred on 24 May 2000, launching the Eutelsat W4 communications satellite into a geosynchronous orbit. [8] All Atlas III launches were made from Space Launch Complex 36B at Cape Canaveral Space Force Station (CCSFS), which at that time was called Cape Canaveral Air Force Station (CCAFS). The Atlas III made its sixth and final flight on 3 February 2005, with a classified payload for the United States National Reconnaissance Office. [9] [10] Although its career was short, Atlas III performed 6 successful missions with no failures.

Proposed derivatives

The GX rocket, formerly under development by Galaxy Express Corporation, was originally intended to use the boost stage of the Atlas III, provided by Lockheed-Martin, and a newly designed upper stage. It would have launched from the Tanegashima Space Center, south of Kyūshū, Japan. In December 2009, the Japanese government decided to cancel the GX project. [11]

The Atlas III first stage was considered as a Removable Propulsion Module (RPM) for the Starbooster concept. [12]

See also

Related Research Articles

<span class="mw-page-title-main">Titan (rocket family)</span> Family of launch vehicles used in U.S. Air Force and space programs (1959–2005)

Titan was a family of United States expendable rockets used between 1959 and 2005. The Titan I and Titan II were part of the US Air Force's intercontinental ballistic missile (ICBM) fleet until 1987. The space launch vehicle versions contributed the majority of the 368 Titan launches, including all the Project Gemini crewed flights of the mid-1960s. Titan vehicles were also used to lift US military payloads as well as civilian agency reconnaissance satellites and to send interplanetary scientific probes throughout the Solar System.

<span class="mw-page-title-main">Centaur (rocket stage)</span> Family of rocket stages which can be used as a space tug

The Centaur is a family of rocket propelled upper stages that has been in use since 1962. It is currently produced by U.S. launch service provider United Launch Alliance, with one main active version and one version under development. The 3.05 m (10.0 ft) diameter Common Centaur/Centaur III flies as the upper stage of the Atlas V launch vehicle, and the 5.4 m (18 ft) diameter Centaur V has been developed as the upper stage of ULA's new Vulcan rocket. Centaur was the first rocket stage to use liquid hydrogen (LH2) and liquid oxygen (LOX) propellants, a high-energy combination that is ideal for upper stages but has significant handling difficulties.

<span class="mw-page-title-main">S-IVB</span> Third stage on the Saturn V and second stage on the Saturn IB

The S-IVB was the third stage on the Saturn V and second stage on the Saturn IB launch vehicles. Built by the Douglas Aircraft Company, it had one J-2 rocket engine. For lunar missions it was fired twice: first for Earth orbit insertion after second stage cutoff, and then for translunar injection (TLI).

<span class="mw-page-title-main">RM-81 Agena</span> American rocket upper stage and satellite bus

The RM-81 Agena was an American rocket upper stage and satellite bus which was developed by Lockheed Corporation initially for the canceled WS-117L reconnaissance satellite program. Following the division of WS-117L into SAMOS and Corona for image intelligence, and MIDAS for early warning, the Agena was later used as an upper stage, and an integrated component, for several programs, including Corona reconnaissance satellites and the Agena Target Vehicle used to demonstrate rendezvous and docking during Project Gemini. It was used as an upper stage on the Atlas, Thor, Thorad and Titan IIIB rockets, and considered for others including the Space Shuttle and Atlas V. A total of 365 Agena rockets were launched between February 28, 1959 and February 1987. Only 33 Agenas carried NASA payloads and the vast majority were for DoD programs.

<span class="mw-page-title-main">Delta II</span> American space launch system

Delta II was an expendable launch system, originally designed and built by McDonnell Douglas, and sometimes known as the Thorad Delta 1. Delta II was part of the Delta rocket family, derived directly from the Delta 3000, and entered service in 1989. There were two main variants, the Delta 6000 and Delta 7000, with the latter also having "Light" and "Heavy" subvariants. During its career, Delta II flew several notable payloads, including 24 Global Positioning System (GPS) Block II satellites, several dozen NASA payloads, and 60 Iridium communication satellites. The rocket flew its final mission, ICESat-2, on 15 September 2018, earning the launch vehicle a streak of 100 successful missions in a row, with the last failure being GPS IIR-1 in 1997. In the late 1990s, Delta II was developed further into the unsuccessful Delta III, which was in turn developed into the more capable and successful Delta IV, though the latter shares little heritage with the original Thor and Delta rockets.

<span class="mw-page-title-main">Delta IV</span> Active expendable launch system in the Delta rocket family

Delta IV was a group of five expendable launch systems in the Delta rocket family introduced in the early 2000s. Originally designed by Boeing's Defense, Space and Security division for the Evolved Expendable Launch Vehicle (EELV) program, the Delta IV became a United Launch Alliance (ULA) product in 2006. The Delta IV was primarily a launch vehicle for United States Air Force (USAF) military payloads, but was also used to launch a number of United States government non-military payloads and a single commercial satellite.

The Saturn I was a rocket designed as the United States' first medium lift launch vehicle for up to 20,000-pound (9,100 kg) low Earth orbit payloads. The rocket's first stage was built as a cluster of propellant tanks engineered from older rocket tank designs, leading critics to jokingly refer to it as "Cluster's Last Stand". Its development was taken over from the Advanced Research Projects Agency in 1958 by the newly formed civilian NASA. Its design proved sound and flexible. It was successful in initiating the development of liquid hydrogen-fueled rocket propulsion, launching the Pegasus satellites, and flight verification of the Apollo command and service module launch phase aerodynamics. Ten Saturn I rockets were flown before it was replaced by the heavy lift derivative Saturn IB, which used a larger, higher total impulse second stage and an improved guidance and control system. It also led the way to development of the super-heavy lift Saturn V which carried the first men to landings on the Moon in the Apollo program.

<span class="mw-page-title-main">Titan IV</span> Expendable launch system used by the US Air Force

Titan IV was a family of heavy-lift space launch vehicles developed by Martin Marietta and operated by the United States Air Force from 1989 to 2005. Launches were conducted from Cape Canaveral Air Force Station, Florida and Vandenberg Air Force Base, California.

<span class="mw-page-title-main">Titan IIIB</span>

Titan IIIB was the collective name for a number of derivatives of the Titan II ICBM and Titan III launch vehicle, modified by the addition of an Agena upper stage. It consisted of four separate rockets. The Titan 23B was a basic Titan II with an Agena upper stage, and the Titan 24B was the same concept, but using the slightly enlarged Titan IIIM rocket as the base. The Titan 33B was a Titan 23B with the Agena enclosed in an enlarged fairing, in order to allow larger payloads to be launched. The final member of the Titan IIIB family was the Titan 34B which was a Titan 24B with the larger fairing used on the Titan 33B.

<span class="mw-page-title-main">Titan IIIC</span> Expendable launch system used by the US Air Force

The Titan IIIC was an expendable launch system used by the United States Air Force from 1965 until 1982. It was the first Titan booster to feature large solid rocket motors and was planned to be used as a launcher for the Dyna-Soar, though the spaceplane was cancelled before it could fly. The majority of the launcher's payloads were DoD satellites, for military communications and early warning, though one flight (ATS-6) was performed by NASA. The Titan IIIC was launched exclusively from Cape Canaveral while its sibling, the Titan IIID, was launched only from Vandenberg AFB.

<span class="mw-page-title-main">Atlas II</span> American rocket

Atlas II was a member of the Atlas family of launch vehicles, which evolved from the successful Atlas missile program of the 1950s. The Atlas II was a direct evolution of the Atlas I, featuring longer first stage tanks, higher-performing engines, and the option for strap-on solid rocket boosters. It was designed to launch payloads into low Earth orbit, geosynchronous transfer orbit or geosynchronous orbit. Sixty-three launches of the Atlas II, IIA and IIAS models were carried out between 1991 and 2004; all sixty-three launches were successes, making the Atlas II a highly reliable space launch system. The Atlas line was continued by the Atlas III, used between 2000 and 2005, and the Atlas V which is still in use.

Delta III was an expendable launch vehicle made by McDonnell Douglas. The vehicle was developed from the highly-successful Delta II to help meet the launch demand of larger satellites. The first Delta III launch was on August 26, 1998. Of its three flights, the first two were failures, and the third, though declared successful, reached the low end of its targeted orbit range and carried only a dummy (inert) payload. The Delta III could deliver up to 3,810 kg (8,400 lb) to geostationary transfer orbit, twice the payload of its predecessor, the Delta II. Under the four-digit designation system from earlier Delta rockets, the Delta III is classified as the Delta 8930.

<span class="mw-page-title-main">Atlas-Centaur</span> Family of space launch vehicles

The Atlas-Centaur was a United States expendable launch vehicle derived from the SM-65 Atlas D missile. The vehicle featured a Centaur upper stage, the first such stage to use high-performance liquid hydrogen as fuel. Launches were conducted from Launch Complex 36 at the Cape Canaveral Air Force Station (CCAFS) in Florida. After a strenuous flight test program, Atlas-Centaur went on to launch several crucial spaceflight missions for the United States, including Surveyor 1, Mariner 4, and Pioneer 10/11. The vehicle would be continuously developed and improved into the 1990s, with the last direct descendant being the highly successful Atlas II.

<span class="mw-page-title-main">Atlas V</span> Expendable launch system

Atlas V is an expendable launch system and the fifth major version in the Atlas launch vehicle family. It was originally designed by Lockheed Martin, now being operated by United Launch Alliance (ULA), a joint venture between Lockheed Martin and Boeing. It is used for DoD, NASA, and Commercial payloads. It is America's longest-serving active rocket. After 87 launches, in August 2021 ULA announced that Atlas V would be retired, and all 29 remaining launches had been sold. As of January 2024, 17 launches remain. Other future ULA launches will use the new Vulcan Centaur rocket.

<span class="mw-page-title-main">Atlas (rocket family)</span> Family of American missiles and space launch vehicles

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 kerosene 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.

<span class="mw-page-title-main">Proton-M</span> Russian heavy lift launcher which uses hypergolic fuel

The Proton-M, (Протон-М) GRAU index 8K82M or 8K82KM, is an expendable Russian heavy-lift launch vehicle derived from the Soviet-developed Proton. It is built by Khrunichev, and launched from sites 81 and 200 at the Baikonur Cosmodrome in Kazakhstan. Commercial launches are marketed by International Launch Services (ILS), and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.

<span class="mw-page-title-main">Atlas I</span>

The Atlas I was a US expendable launch system manufactured by General Dynamics in the 1990s to launch a variety of satellites. It was largely a commercial rebrand of the Atlas G, but did feature several electrical and guidance improvements. Atlas I did not feature any major payload capacity improvements over its predecessor but did offer a larger payload fairing option. Eleven launches took place, with three failures.

<span class="mw-page-title-main">Atlas G</span> Expendable launch vehicle

The Atlas G, also known as Atlas G Centaur-D1AR was an American expendable launch system derived from the Atlas-Centaur. It was a member of the Atlas family of rockets and was used to launch seven communication satellites during the mid to late 1980s. Atlas G consisted of an improved Atlas core with modernized avionics and stretched propellant tanks. The Centaur stage also had several updated components and other technical improvements. Atlas G flew 7 times, with all missions aiming to go to a geostationary transfer orbit. It was replaced by the near-identical Atlas I, which had an improved guidance system and offered a larger payload fairing.

The Atlas SLV-3, or SLV-3 Atlas was an American expendable launch system derived from the SM-65 Atlas / SM-65D Atlas missile. It was a member of the Atlas family of rockets.

<span class="mw-page-title-main">Vulcan Centaur</span> United Launch Alliance launch vehicle

Vulcan Centaur is a two-stage-to-orbit, expendable, heavy-lift launch vehicle by United Launch Alliance (ULA). It is principally designed to meet launch demands for the U.S. government's National Security Space Launch (NSSL) program for use by the United States Space Force and U.S. intelligence agencies for national security satellite launches. It will replace both of ULA's existing heavy-lift launch systems due to their retirement. Vulcan Centaur will also be used for commercial launches, including an order for 38 launches from Kuiper Systems.

References

  1. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 "Atlas Launch System Payload Planner's Guide" (PDF). Lockheed Martin. Archived from the original (PDF) on 21 April 2015. Retrieved 12 July 2022.
  2. 1 2 "Space Launch Report: Atlas III Data Sheet". 1 December 2005. Archived from the original on 21 March 2022. Retrieved 9 March 2024.
  3. "Lockheed Martin Selects RD-180 to Power Atlas IIAR". International Launch Services. 17 January 1996. Retrieved 9 March 2013.
  4. "Atlas IIIA". Encyclopedia Astronautica. Archived from the original on 1 July 2013. Retrieved 8 March 2007.
  5. 1 2 3 United Launch Alliance. "The Centaur Upper Stage Vehicle" (PDF). alalaunch.com. Retrieved 16 July 2022.
  6. "last-4m". 10 November 2022.
  7. United Launch Alliance. "Atlas V". ulalaunch.com.
  8. Gunter D. Krebs. "Atlas-3A (Atlas-IIIA)". Gunter's Space Page. Retrieved 6 June 2020.
  9. Ray, Justin (3 February 2015). "Last Atlas 3 rocket launches a pair of spy satellites". Spaceflight Now. Retrieved 6 June 2020.
  10. Plain, Charlie. "NASA – Out With a Bang!". nasa.gov. Retrieved 6 June 2020.PD-icon.svg This article incorporates text from this source, which is in the public domain .
  11. "Japan scraps GX rocket development project". iStockAnalyst. 16 December 2009. Archived from the original on 6 March 2014. Retrieved 16 December 2009.
  12. "Starcraft Boosters, Inc. - The StarBooster System - A Cargo Aircraft for Space" (PDF). October 1999.
Atlas III
Atlas III Centaur.jpg
The maiden flight of the Atlas III
FunctionMedium expendable launch vehicle
Manufacturer Lockheed Martin
Country of originUnited States
Size
Height52.8 m (173 ft)
Diameter3.05 m (10.0 ft)
Mass214,338 kg (472,534 lb)
Stages2
Capacity
Payload to 185 km 28.5° Low Earth orbit
MassIIIA: 8,686 kg (19,149 lb)
IIIB: 10,759 kg (23,720 lb) [1]
Total launches6
(IIIA: 2, IIIB: 4)
Success(es)6
(IIIA: 2, IIIB: 4) [2]
First flightIIIA: 24 May 2000
IIIB: 21 February 2002
Last flightIIIA: 13 March 2004
IIIB: 3 February 2005
First stage
Powered by1 RD-180
Maximum thrust4,148.7 kN (932,700 lbf)
Specific impulse 311 s (3.05 km/s)
Burn time132 seconds
Propellant RP-1 / LOX