The CCB of Atlas V AV-021 is erected at the Vertical Integration Facility of SLC-41 ahead of the launch of the Solar Dynamics Observatory |
|
| Manufacturer | Lockheed Martin (1998–2006) United Launch Alliance (2006—) |
|---|---|
| Country of origin | United States |
| Rockets | Atlas V (stage 1) Atlas V Heavy (boosters, cancelled) GX (stage 1, cancelled) |
| Size | |
| Height | 32.46 metres (106.5 ft) |
| Diameter | 3.81 metres (12.5 ft) |
| Mass | 306,914 kilograms (676,630 lb) |
| Engine details | |
| Engines | One RD-180 |
| Thrust | 4,152 kilonewtons (933,000 lbf) |
| Burn time | 253 seconds |
| Fuel | LOX/RP-1 |
The Common Core Booster (CCB) is an American rocket stage, which is used as the first stage of the 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 programme was cancelled in late 2009.
The Common Core Booster is 32.46 metres (106.5 ft) long, has a diameter of 3.81 metres (12.5 ft) and is powered by a single RD-180 engine burning RP-1 and liquid oxygen.[1]
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.[2] 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.[3] As of September 2010, the Atlas V has made twenty two flights, all of which have used a single Common Core Booster.
|
||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||||