Manufacturer | Lockheed Martin (1998–2006) United Launch Alliance (2006—) |
---|---|
Country of origin | United States |
Used on | Atlas V (stage 1) Atlas V Heavy (boosters, cancelled) GX (stage 1, cancelled) |
General characteristics | |
Height | 32.46 m (106.5 ft) |
Diameter | 3.81 m (12.5 ft) |
Propellant mass | 284,089 kg (626,309 lb) |
Empty mass | 21,054 kg (46,416 lb) (V 400 Series) 21,351 kg (47,071 lb) (V 500 Series) [1] |
Propulsion | |
Powered by | 1 RD-180 |
Maximum thrust | 3,827 kN (860,000 lbf) (SL) 4,152 kN (933,000 lbf) (vac) |
Burn time | 253 s |
Propellant | LOX/RP-1 |
The Common Core Booster (CCB) is a rocket stage, which is used as the first stage of the American Atlas V rocket as part of its modular design. It was also intended that two additional CCBs would be used as boosters on the Atlas V Heavy, however this configuration has not been developed. Use of a Common Core Booster as the first stage of the Japanese GX was also planned; however, this program was cancelled in late 2009.
The Common Core Booster is 32.46 m (106.5 ft) long, has a diameter of 3.81 m (12.5 ft) and is powered by a single RD-180 engine burning RP-1 and liquid oxygen. [2]
Testing of the CCB and its RD-180 engines was conducted in the United States at the Marshall Space Flight Center, and in Khimki, Russia. The test programme concluded with the final engine test in December 2001. [3] The first launch of a Common Core Booster was the maiden flight of the Atlas V, which was launched from Space Launch Complex 41 at the Cape Canaveral Air Force Station on 21 August 2002. [4] As of November 2020, the Atlas V has made 86 flights, all of which have used a single Common Core Booster. [5]
Energia was a 1980s super-heavy lift launch vehicle. It was designed by NPO Energia of the Soviet Union as part of the Buran program for a variety of payloads including the Buran spacecraft. Control system main developer enterprise was the Khartron NPO "Electropribor". The Energia used four strap-on boosters each powered by a four-chamber RD-170 engine burning kerosene/LOX, and a central core stage with four single-chamber RD-0120 (11D122) engines fueled by liquid hydrogen/LOX.
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