.
.
Height (m):
22.9
14.6 (with payload fairing)
(included with payload)
39.8
Diameter (m):
3.05
3.05
-
-
Launch weight (kg):
128 736
17 674
-
146 914
Propulsion system:
MA-5
-
-
-
Powerplant:
2 booster engines
Pratt & Whitney (2)
Thiokol
-
1 sustainer engine
RL-10A 3-3
TE-M-364 4
-
2 vernier engines
-
-
-
Thrust (newtons):
1 919 300
131 200
65 866
2 050 500 (2 116 366 with third
stage)
Burn time (sec.):
230
450 (max.)
44
-
Propellant:
LOX/RP-1
LOX/LH2
solid
-
Payload capacity:
4500 kg to earth orbit/1800 to
synchronous orbit
900 kg to Venus or Mars
Origin:
Air Force missile system
NASA-General Dynamics design
NASA-Thiokol design
-
.
Contractors:
Rocketdyne Div., Rockwell Corp.:
propulsion system Convair Div.,
General Dynamics: prime
Pratt & Whitney: engines Convair
Div.,General Dynamics: prime
Thiokol Corp.: engine McDonnell
Douglas Astronautics Co. airframe
Program manager:
F. Robert Schmidt, NASA Hq.
Project managers:
Daniel J. Schramo, Henry O. Slone,
Lawrence J. Ross, Lewis Research Center
How utilized:
Mariner, Pioneer, Intelsat, Pioneer
Venus, ATS, OAO, Comstar, HEAO, Fltsatcom
Remarks:
The Atlas and the Centaur stages were
both upgraded during NASA's second 10 years. The Atlas
SLV-3D model was introduced in 1973, as was the Centaur
D-IA. The optional third stage motor was used with the
Atlas-Centaur combination four times: Pioneer 10, Pioneer
11, Intelsat IV F-7, and Mariner 10. It was attached to the
aft of the spacecraft.
See also:
Volume 2.