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Archive-name: space/launchers
Last-modified: $Date: 92/10/31 17:37:49 $

ORBITAL AND PLANETARY LAUNCH SERVICES

If anyone has more accurate or more complete information, please post
it and copy jim@pnet01.cts.com (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