Atlas LV-3B

Atlas LV-3B
An Atlas D LV-3B launching Mercury-Atlas 6
FunctionCrewed expendable launch system
ManufacturerConvair
Country of originUnited States
Size
Height28.7 metres (94.3 ft)
Diameter3.0 metres (10.0 ft)
width over boost fairing 4.9 metres (16 ft)
Mass120,000 kilograms (260,000 lb)
Stages
Capacity
Payload to LEO
Mass1,360 kilograms (3,000 lb)[1]
Launch history
StatusRetired
Launch sitesCCAFS LC-14
Total launches9
Success(es)7
Failure(s)2
First flight29 July 1960
Last flight15 May 1963
Boosters
No. boosters1
Powered by2 Rocketdyne XLR-89-5
Maximum thrust1,517.4 kilonewtons (341,130 lbf)
Burn time135 seconds
PropellantRP-1/LOX
First stage
Diameter3.0 metres (10.0 ft)
Powered by1 Rocketdyne XLR-105-5
Maximum thrust363.22 kilonewtons (81,655 lbf)
Burn time5 minutes
PropellantRP-1/LOX

The Atlas LV-3B, Atlas D Mercury Launch Vehicle or Mercury-Atlas Launch Vehicle, was a human-rated expendable launch system used as part of the United States Project Mercury to send astronauts into low Earth orbit. Manufactured by Convair, it was derived from the SM-65D Atlas missile, and was a member of the Atlas family of rockets. With the Atlas having been originally designed as a weapon system, testing and design changes were made to the missile to make it a safe and reliable launch vehicle. After the changes were made and approved, the US launched the LV-3B nine times, four of which had crewed Mercury spacecraft.

  1. ^ Wade, Mark. "Atlas LV-3B / Mercury". Encyclopedia Astronautica. Archived from the original on 11 November 2011. Retrieved 24 November 2011.