Aeronautics and Space Report of the President FY 1995 Activities


Appendix D

U.S. Space Launch Vehicles

(continued)

Vehicle Stages:
Engine/Motor
Propellanta Thrust
(kilo-
newtons)bc
Max. Dia
x Height
(m)
185-Km
Orbit
Geosynch.
Transfer
Orbit
Sun-
Synch.
Orbite
First
Launchf
Titan II


3.05x42.9 1905e 1988, [1964, Titan II SLV Titan II Gemini]

1. LR-87-AJ-5 (2)
2. LR-91-AJ-5
N204/A-50
N204/A-50
1045.0
440.0
3.05x21.5
3.05x12.2




Titan III


3.05x47.3 14515 5000l 1989, Titan III [1964, Titan IIIA]





7300e



0. Titan III SRM (2)
(5-1/2 segments)
1. LR87-AJ-11 (2)
2. LR91-AJ-11
Solid
N204/A-50
N204/A-50
6210.0
1214.5
462.8
3.11x27.6
3.05x24.0
3.05x10.0




Titan IV


3.05x62.2 17700 6350m 1989 Titan IV





14110e



0. Titan IV SRM (2)
(7 segments)
1. LR87-AJ-11 (2)
2. LR91-AJ-11
Solid
N204/A-50
N204/A-50
7000.0
1214.5
462.8
3.11x34.1
3.05x26.4
3.05x10.0




Titan IV/ Centaur


4.3x62.2 5760a 1994, Titan IV Centaur

0. Titan IV SRM (2)
(7 segments)
1. LR87-AJ-11 (2)
2. LR91-AJ-11(1)
3. Centaur: RL-10A-3-3A
4. SRMU
(3 segments)
Solid
N204/A-50
N204/A-50
LOX/LH2
7000.0
1214.5/engine
462.5
73.4
7690
3.11x34.1
3.05x26.4
3.05x10.0
4.3x9.0
3.3x34.3




Space Shuttlen


23.79x56.14h 24900o 5900p 1981, Columbia

1. SRB: Shuttle SRB (2)
2. LR91-AJ-11(1)
2. Orbiter/ET:SSME (3)
3. Orbiter/OMS: OMS
engines (2)
Solid
LOX/LH2
N204/MMH
LOX/LH2
11790.0(SL)
1668.7(SL)
26.7
3.70x45.46
8.41x47.00 (ET)
23.79x37.24h (orbiter)
23.79x37.24h





——Max. Payload (kg)d ——
Vehicle Stages:
Engine/Motor
Propellanta Thrust
(kilonewtons)bc
Max. Dia
x Height
(m)
185-Km
Orbit
Geosynch.
Transfer
Orbit
Sun-
Synch.
Orbite
First
Launchf
NOTES:
aPropellant abbreviations used are as follows:
A-50 = Aerozine 50 (50% Monomethyl Hydrazine,
50% Unsymmetrical Dimethyl Hydrazine)
RP-1 = Rocket Propellant 1 (kerosene)
Solid = Solid Propellant (any type)
LH2 = Liquid Hydrogen
LOX = Liquid Oxygen
MMH = Monomethyl Hydrazine
N204 = Nitrogen Tetroxide

bThrust at vacuum except where indicated at sea level (SL).

cThrust per engine. Multiply by number of engines for thrust per stage.

dInclination of 28.5š except where indicated.

e Polar launch from Vandenberg AFB, CA.

f First successful orbital launch [ditto of initial version].

g First launch was a failure

h Diameter dimension represents vehicle wing span.

iApplies to Delta II-7925 version only.

j Two Castor IVA motors ignited at lift-off. Two Castor IVA motors ignited at approximately 57 seconds into flight.

kWith TE-M-364-4 upper stage.

lWith Transfer Orbit Stage (TOS).

mWith appropriate upper stage.

nSpace Shuttle Solid Rocket Boosters fire in parallel with the Space Shuttle Main Engines (SSME), which are mounted on the aft end of the Shuttle Orbiter Vehicle and burn fuel, and oxidizer from the External Tank. The boosters stage first, with SSME'scontinuing to fire. The External Tank stages next, just before the orbiter attains orbit.The Orbiter Maneuvering Subsystem is then used to maneuver or change the orbit of the Orbiter Vehicle.

o204 km circular orbit.

pWith Inertial Upper Stage (IUS) or Transfer Orbit Stage (TOS).

qTitan IV/Centaur is designed for 3 burns directly to geosynchronous orbit.

rThe first Taurus launch used a Peacekeeper first stage as stage 0 in 1994.

NOTE: Data should not be used for detailed NASA mission planning without concurrence of the Director of Space Transportation System Support Programs.


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Curator: Lillian Gipson
Last Updated:September 5, 1996
For more information contact Steve Garber, NASA History Office,
sgarber@hq.nasa.gov