Conference 7.286::space

    Here is all my knowledge:
    
    ITEM                	FACT          
    Orbiter Dry Weight    	78,100lbs(35,500Kg)
    Orbiter Fuel Cap		For the main engines none, for OMS ?
    Orbiter Max Payload		32 tons
    Orbiter Main Engine(SSME) 	375,000lbs apiece 100% at sea level
    thrust
    Orbiter OMS(Orb. Man. Sys.) 2,000 lbs apiece
    External Tank(ET) Dry Weight78,100 lbs
    ET Fuel Cap.		Oxygen-143,000 gallons, Hydrogen 383,000
    SRB Dry Weight		185,000lbs each
    SRB Fuel Cap.		?
    SRB Thrust			2,650,000lbs each at sea level
    SRB Brun Time		On Avg 2 Min 10 Sec
    Launch Weight		4.4 million lbs(2 million Kgs)
    Speed at SRB Sep		?
    SSME Burntime		8 min 38 sec normal longer for ATO abort
    SSME Retrofire		none, the OMS retrofires for 2 to 3 min
    Re-entry speed		16,465mph
    Landing Glidescope		22 deg
    Landing Speed		215 mph
    
    As to landing sys here it is:
    	From Blackout to 18,00 ft TACAN is used or tactical air navigation.
    this gives distance and bearing readings every 37 seconds
    	Once the orbiter reaches the Heading Alignment cylinder or HAC this
    gives elevation, the angle of azimuth(left and right) and range to
    runway
    	The shuttle also has two onboard radar altimeters for precise
    altitude information.
    
    	Well that is it, hope I helped.
    
    		-Matt
    

    Sorry! I listed the Orbiter Dry weight and the ET Dry Weight as the
    same. Here is the real info: ET Dry Weight-78,100lbs(35,500Kg), Orbiter
    Dry Weight-165,000lbs(75,000Kg)
    
    		-Matt
    

    re: .1+.2
    
    Matt, thank you very much for the details, they will be of great help
    once the shuttle-model production line is ramped up. I've been delayed
    a bit in reviewing this entry due to power plant problems. Now it seems
    as if it would be a good idea to await FLIGHT version 2.4 for the first
    shuttle launch, but the manufacturing process is begun - with good
    valid data; thanks to you.
    
    Nis

    Any Time
    
    

    
    
    I have recently started playing around with Earth to Orbit performance
    numbers for various things, Delta Clipper etc, and naturally I use the
    Space Shuttle for all comparations.   I would help greatly if the fuel
    masses and fuel exaust velocities   were added to info in the previous
    replies.
    
    I know that fuel gallons are given, but not knowing the density of 
    liquid H2 or O2 that leaves me nowhere. 
    
    Here is my guesses:
    
    Engine	Exaust V (Km/s)		Fuel Mass (Metric Tons)
    ------	---------------		-----------------------
    SRB 	3			550 (each)
    SSME	4.5			700
    OMS		3			 10 (each)
    
    
    * Also, each OMS thrust "must be" 20,000 lbs  rather then  2,000 lbs
    
    Does, anyone have the data ?
    
    Gil

RE: Note 597.5
    
>    * Also, each OMS thrust "must be" 20,000 lbs  rather then  2,000 lbs

I'm sure the OMS engines are less that 20,000 lbs thrust. I vaguely recall a
figure of 6,000 lbs (probably the sum of both), but I'm not very certain of
that. The 2,000 lbs figure (for a single OMS engine) may well be correct.
						-- Tom
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Each OMS engine can produce 6,000 lbs. of thrust.