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Atlas·Convair

Atlas V 421

retired
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Specifications

Status
retired
Height
58.3 m
Diameter
3.8 m
Mass
433,000 kg
Stages
2
Thrust
5,493 kN
Payload to LEO
14,067 kg
Payload to GTO
6,890 kg
First flight
2007-10-11
Total launches
9
Success / Fail
9 / 0

Atlas V is an expendable launch system in the Atlas rocket family. It was formerly operated by Lockheed Martin and is now operated by United Launch Alliance (ULA), a joint venture with Boeing. Each Atlas V rocket uses a Russian-built RD-180 engine burning kerosene and liquid oxygen to power its first stage and an American-built RL10 engine burning liquid hydrogen and liquid oxygen to power its Centaur upper stage. The RD-180 engines are provided by RD Amross, while Aerojet Rocketdyne provides both the RL10 engines and the strap-on boosters used in some configurations. The 421 version uses a 4m wide fairing, 2 solid rocket boosters and one engine on the Centaur stage.

Propulsion

Boosters

GEM 631,663 kN
solid (HTPB) · solid
Northrop GrummanIsp 279s (vac)since 20200–5 strap-ons

First stage

RD-1803,830 kN
RP-1 / LOX · staged-combustion
NPO EnergomashIsp 338s (vac)since 2000

Second stage

RL10110 kN
LH2 / LOX · expander
Aerojet RocketdyneIsp 451s (vac)since 1963Centaur

Payloads it launched

14 loaded
SBIRS GEO-6 (USA 336)
GEO
SBIRS GEO-5 (USA 315)
GEO
TDO-3
LEO
TDO-4
LEO
USA 279
GEO
USA 269
GEO
MORELOS 3
GEO
MMS 4
HEO
MMS 1
HEO
MMS 2
HEO
MMS 3
HEO
WGS F2 (USA 204)
GEO
ICO G1
GEO
WGS F1 (USA 195)
GEO