|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 28.5 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.