pyle@ut-ngp.UUCP (04/21/84)
According to my references, here are the specs on the STS propulsion
systems:
Solid Rocket Booster (SRB, 2 per flight):
Used from T+0:0:02.64 (i.e., 2.64 seconds after check of main
engine status) until T+0:02:00, separate at T+0:02:07
Length: 149 feet, Diameter: 12 feet,
Weight at launch: 1,300,000 pounds each,
Thrust at launch: 2,650,000 pounds each
Propellants: fuel - aluminum powder (16%), oxidizer - ammonium
perchlorate (69.83%), catalyst - iron oxide powder (0.17%),
binder and curing agents - (14%)
SRB nozzles gimbal up to 6 degrees for steering under power
of SRB Auxillary Power Unit (APU)
Space Shuttle Main Engine (SSME, 3 per shuttle):
Typically operate from T-0:0:03 until T+0:08:38
Rated thrust: 375,000 pounds, variable from 65 to 109% of
rated value
Designed to operate 7.5 hours between major overhauls,
in reality this has not been met
Propellants: hydrogen and oxygen with final burn ratio of 1:6
Orbital Maneuvering System (OMS, 2 engines per shuttle):
Operates during orbital insertion, deorbit burn, and
as needed for orbital changes
Thrust: 6,000 pounds each
Propellants: fuel - monomethyl hydrazine, oxidizer -
nitrogen tetroxide
Length: 77 inches, weight: 260 pounds, gimbaled in
pitch and yaw
Reaction Control System (RCS):
Primary thrusters: 38 engines with 870 pound thrust
Secondary thrusters: 6 engines with 25 pound thrust
RCS thrusters are grouped in three modules: one in nose,
and in each OMS pod
Propellants: same as OMS engines
Keith Pyle
UUCP: . . .{ihnp4,seismo,ctvax,kpno,gatech}!ut-sally!ut-ngp!pyle
ARPA: pyle@ut-ngp