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sci.space FAQ - Orbital and Planetary Launch Servi
Archive-name: space/launchers
Last-modified: $Date: 92/09/02 14:48:15 $
ORBITAL AND PLANETARY LAUNCH SERVICES
If anyone has more accurate or more complete information, please post
it and copy [email protected] (Jim Bowery), who maintains the primary
copy of this item. Don't forget to include the source of the
information.
PAYLOAD(LBS) DELIVERED TO
COMPANY/VEHICLE $M LEO GTO GEO ESCAPE U.STAGE LAUNCHFAIL(1)
MM/Titan4[H] 296 47000 .... 10300 .... Centaur .... ....
MM/Titan4 277 49000 15000 5800 .... IUS .... ....
MM/Titan3 160 32500 12474 4100 .... TOS .... ....
AS/Arian44L[H] 110 21164 9259 5500 .... none .... ....
GD/Atlas2 80 15700 6200 3000 .... Centaur .... ....
MD/Delta2 52 11100 4010 2000 2816[S] PAMD[H] .... ....
GW/LongMarch3 45 6614 2866 1433 .... none .... ....
EPAC/EagleS2[E] 30 10000(2)5128 3374 ....(4) USTM(3) 0 0
OSC/Taurus[S] 17 2703 .... .... 374 .... 0 0
EPAC/EagleS1[E] 15 6000 .... .... ....(4) USTM 0 0
AMROC/Aquila[S] 10 2000 1467 .... .... none 0 0
SSI/Conestoga 10 1500(5) 900(6) 550(7) .... 0 0
OSC/Pegasus[H] 9.7 750 .... .... .... none 2 1
EPAC/Eagle[E] 6.7 3000 .... .... .... USTM 0 0
(1) For launches where reflight insurance is issued, the fraction of the
launch cost indemnified is the failure level for that flight.
For launches where reflight insurance is not issued, a rough
estimate is made as to the fraction of the launch cost that
would have been indemnified.
(2) LEO given is 300nmi altitude [S].
(3) The bipropellant (Isp=323) USTM has a dry weight of approximately 1600LBS
which must be subtracted from the total weight to determine weight
available for electronics, power, communication and fuel. The USTM
provides station-keeping and course correction in addition to
transfer and apogee burns.
(4) According to [S] escape requires 170kg MMH/NTO fuel with USTM.
(5) 200nmi altitude 37.9d inclination [S].
(6) 400nmi altitude [S].
(7) Includes Conestoga apogee kick stage weight.
REFLIGHT
VEHICLE POLARLBS(9) INSURANCE(%) ACCURACY PAD WEIGHT
MM/Titan4[H] .... .... .... 1910449
MM/Titan4 .... .... .... 1885525
MM/Titan3 .... .... .... 1492200
AS/Arian44L .... .... .... 1033000
GD/Atlas2 12400 .... .... 360600
MD/Delta2 8401 .... .... 450000
GW/LongMarch3 .... .... .... 444400
EPAC/EagleS2[E] .... 18 1.4km(9) 268145
OSC/Taurus[S] 2140 .... .... ....
EPAC/EagleS1[E] .... 18 1.4km(9) ....
AMROC/Aquila[S] 1467 .... .... ....
SSI/Conestoga 900 .... 9.3km(10) ....
OSC/Pegasus[S] 649 .... .... ....
EPAC/Eagle .... 18 .... 99134
(9) For unknown data, conservative figures for polar orbit can be
estimated by dividing LEO weight by 2.
(10) Circular orbit and <0.02d inclination error to 3 sigma [S].
(11) Reduced payload for upper stage with thrust vector control. 1 sigma [S].
Figures given as "...." are to be included in a future release.
Information sources are indicated by a source code within square brackets.
For example [H] means the associated information and subsequent information
comes from the 1989 Hughes Corp. Survey with dollars given in 1989 dollars.
Source codes: H = 1989 Hughes Corp. Survey
E = 9/1991 E'Prime Aerospace Corp. report
S = "A Status Report on the Availability of Expendable
Launch Vehicles for Small Solar System
Exploration Payloads", Jim McAdams, Science
Applications International Corp. 3/31/1991
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