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From: pyle@ut-ngp.UUCP
Newsgroups: net.columbia
Subject: Shuttle Propulsion Specs
Message-ID: <526@ut-ngp.UUCP>
Date: Fri, 20-Apr-84 21:15:00 EST
Article-I.D.: ut-ngp.526
Posted: Fri Apr 20 21:15:00 1984
Date-Received: Sun, 22-Apr-84 09:29:43 EST
Organization: Comp. Center, Univ. of Texas at Austin
Lines: 60

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

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