SPACE LAUNCH VEHICLES

SPACE LAUNCH VEHICLES

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Abbreviations / Glossary
Aerozine 50: 50% UDMH, 50% Hydrazine CEO: Close Earth Orbit CO: Circular Orbit GO: Geostationary Orbit GTO: Geostationary Transfer Orbit HTP: High Test Peroxide Hydyne: 60% UDMH, 40% Diethylene-Triamine IRFNA: Inhibited Red Fuming Nitric Acid IWFNA: Inhibited White Fuming Nitric Acid LEO: Low Earth Orbit	LH2: Liquid Hydrogen LO2: Liquid Oxygen MMH: Monomethyl Hydrazine N2O4: Nitrogen Tetroxide PO: Polar Orbit RJ-1: Hydrocarbon fuel (kerosene) RP-1: Hydrocarbon fuel (kerosene) SSO: Sun-Synchronous Orbit SSPO: Sun-Synchronous Polar Orbit UDMH: Unsymmetrical Dimethyl Hydrazine

NAME	MASS lb (kg)	S	PROPELLANT	THRUST lb (kg)	REMARKS
CHINA
Long March-1D (CZ-1D)	176,000 (80,000)	1 2 3	Nitric Acid/UDMH N2O4/UDMH Solid	410,000 (125,000) 66,000 (30,000) 4,400 (2,000)	CZ-1 was the original Chinese launch vehicle used in 1970-71. CZ-1D can orbit 1,650 lb (750 kg) to 57 deg 186 miles (300 km).
Long March-2C (CZ-2C) 1975	421,000 (191,000)	1 2	N2O4/UDMH N2O4/UDMH	697,000 (316,000) 171,300 (77,700)	Derived from DF-5 ICBM; CZ-2A used only once. Can place 4,850 lb (2,200 kg) into 63 deg 124 miles (200 km) orbit.
Long March-2D (CZ-2D) 1992	467,000 (212,000)	1 2	N2O4/UDMH N2O4/UDMH	697,000 (316,000) 171,300 (77,700)	Up-rated CZ-2C under study but status unclear; compatible with US PAM-D upper stage. 8,600 lb (3,900 kg) to 28.5 deg 124 miles (200 km) orbit.
Long March-2E (CZ-2E) 1990	1,019,000 (463,000)	1 2	N2O4/UDMH N2O4/UDMH	1,422,000 (644,800) 171,300 (77,700)	Up-rated CZ-2C compatible with US shuttle upper stages for GO missions. 17,600 lb (8,000 kg) to 28.5 deg 124 miles (200 km).
Long March-3 (CZ-3) 1984	445,000 (202,000)	1 2 3	N2O4/UDMH N2O4/UDMH LO2/LH2	695,800 (315,600) 171,300 (77,700) 10,000 (4,500)	CZ-2C with high energy third stage. 3,100 lb (1,400 kg) to 31 deg 124-22,245 miles (200-35,800 km).
Long March-3A (CZ-3A) 1994	529,000 (240,000)	1 2 3	N2O4/UDMH N2O4/UDMH LO2/LH2	695,800 (315,600) 171,300 (77,700) 18,000 (8,000)	Improved CZ-3 vehicle under development. 5,500 lb (2,500 kg) to 28.5 deg 124-22,245 miles (200-35,800 km).
Long March-4A (CZ-4A) 1988	549,000 (249,000)	1 2 3	N2O4/UDMH N2O4/UDMH N2O4/UDMH	695,800 (315,600) 171,300 (77,700) 66,000 (30,000)	CZ-2C and possible CZ-1 technology combined for a vehicle specifically for SSO launches. 8,800 lb (4,000 kg) to 97.8 deg 124 miles (200km); 2,450 lb (1,150 kg) to 97.8 deg 620 miles (1,000 km).
EUROPE
Ariane 1 1979	458,640 (208,000)	1 2 3	N2O4/UDMH N2O4/UDMH LO2/LH2	540,225 (245,000) 154,350 (70,000) 13,230 (6,000)	Derived from Diamant technology. Launched CAT etc. Payload into GTO 3,748 lb (1,700 kg).
Ariane 2 1986	474,000 (215,000)	1 2 3	N2O4/UDMH N2O4/UDMH LO2/LH2	588,955 (267,100) 173,090 (78,500) 13,230 (6,000)	Derived from Ariane 1. Combustion pressure raised. Payload into GTO 4,410 lb (2,000 kg).
Ariane 3 1984	516,000 (234,000)	0 1 2 3	Solid N2O4/UDMH N2O4/UDMH LO2/LH2	317,500 (144,000) 588,955 (267,100) 173,090 (78,500) 13,230 (6,000)	Derived from Ariane 2. Two strap-on boosters added to 1st stage. Payload into GTO 5,182 lb (2,350 kg).
Ariane 4 (40) 1990	535,700 (243,000)	1 2 3	N2O4/UH25 N2O4/UH25 LO2/LH2	674,600 (306,000) 179,450 (81,400) 14,100 (6,400)	Ariane 4 is a modular vehicle, the 40 version being the basic vehicle. 4,200 lb (1,900 kg) to GTO, 5,950 lb (2,700 kg) to SSO and 10,500 lb (4,600 kg) to LEO.
Ariane 4 (42P) 1990	705,700 (320,000)	0 1 2 3	Solid N2O4/UH25 N2O4/UH25 LO2/LH2	292,300 (132,600) 674,600 (306,000) 179,450 (81,400) 14,100 (6,400)	5,700 lb (2,600 kg) to GTO, 7,500 lb (3,400 kg) to SSO, 13,200 lb (6,000 kg) to LEO.
Ariane 4 (44P) 1991	783,000 (355,000)	0 1 2 3	Solid N2O4/UH25 N2O4/UH25 LO2/LH2	584,700 (265,200) 674,600 (306,000) 179,450 (81,400) 14,100 (6,400)	6,600 lb (3,000 kg) to GTO, 9,000 lb (4,100 kg) to SSO, 14,300 lb (6,500 kg) to LEO.
Ariane 4 (42L) 1993	800,000 (363,000)	1 0 2 3	N2O4/UH25 N2O4/UH25 N2O4/UH25 LO2/LH2	336,900 (152,800) 674,600 (306,000) 179,450 (81,400) 14,100 (6,400)	7,100 lb (3,200 kg) to GTO, 9,900 lb (4,500 kg) to SSO, 15,400 lb (7,000 kg) to LEO.
Ariane 4 (44LP) 1988	930,000 (420,000)	0 1 2 3	N2O4/UH25 Solid N2O4/UH25 N2O4/UH25 LO2/LH2	336,900 (152,800) 292,300 (132,600) 674,600 (306,000) 179,450 (81,400) 14,100 (6,400)	8,200 lb (3,700 kg) to GTO, 11,000 lb (5,000 kg) to SSO, 15,400 lb (7,000 kg) to LEO.
Ariane 4 (44L) 1989	1,065,000 (483,000)	0 1 2 3	N2O4.UH25 N2O4/UH25 N2O4/UH25 LO2/LH2	674,000 (305,600) 674,600 (306,000) 179,450 (81,400) 14,100 (6,400)	9,300 lb (4,200 kg) to GTO, 13,200 lb (6,000 kg) to SSO, 15,400 lb (7,000 kg) to LEO. Launched Superbird A and DFS Kopernikus 1 on 5-Jun-89.
Ariane 5 1996	1,583,000 (718,000)	0 1 2	Solid N2O4/MMH LO2/LH2	2,954,000 (1,340,000) 229,000 (104,000) 4,400 (2,000)	40,000 lb (18,000 kg) to 28.5 deg 310 miles (500 km), 15,000 lb (6,800 kg) to GTO. All data for this vehicle are provisional.
Europa I 1964	274,000 (124,265)	1 2 3	LO2/Kerosene N2O4/UDMH N2O4/UDMH+N2H4	302,085 (137,000) 59,535 (27,000) 5,250 (2,380)	Derived from Blue Streak LRBM. Payload into CEO 2,000 lb (907 kg). 3 launches from Woomera--failed.
Europa II 1971	246,000 (111,565)	1 2 3 4	LO2/Kerosene N2O4/UDMH N2O4/UDMH+N2H4 Solid	302,085 (137,000) 59,535 (27,000) 5,250 (2,380) 9,260 (4,200)	Payload into CEO 2,526 lb (1,150 kg); into GO 375 lb (170 kg). One satellite from Kourou--failed. Project abandoned.
FRANCE
Diamant A 1965	39,625 (17,970)	1 2 3	Nitirc Acid/Turps Solid Solid	66,150 (30,000) 33,075 (15,000) 11,685 (5,300)	Launched Asterix, etc. Payload into CEO 176 lb (80 kg).
Diamant B 1970	55,000 (24,945)	1 2 3	N2O4/UDMH Solid Solid	77,175 (35,000) 31,970 (14,500) 11,025 (5,000)	Launched DIAL, People and D2. Payload into 186 mile (300 km) EO 353 lb (160 kg).
Diamant BP4 1975	60,640 (27,500)	1 2 3	N2O4/UDMH Solid Solid	88,200 (40,000) 39,690 (18,000) 11,025 (5,000)	Launched Starlette, Pollus and Castor, Aura. Payload into 186 mile (300 km) EO 441 lb (200 kg). Program ended after three launches, 1975.
INDIA
Satellite Launch Vehicle (SLV) 3 1979	37,300 (16,900)	1 2 3 4	Solid Solid Solid Solid	140,000 (63,500) 60,000 (27,300) 20,000 (9,200) 6,000 (2,700)	First satellite orbited in 1980 after failure in 1979. 92 lb (42 kg) to 45 deg 280-620 miles (450-1,000 km). Third flight partial failure, final flight (1983) success.
Augmented Satellite Launch Vehicle (ASLV) 1987	86,000 (39,000)	1 2 3 4 5	Solid Solid Solid Solid Solid	265,000 (120,300) 158,000 (71,600) 68,000 (31,000) 20,000 (9,200) 7,900 (3,600)	Launch attempts in 1987 and 1988 failed and program suspended. 330 lb (150 kg) to 45 deg 248 miles (400 km).
Polar Satellite Launch Vehicle (PSLV) 1993	606,300 (275,000)	0 1 2 3 4	Solid Solid N2O4/UDMH Solid N2O4/MMH	796,000 (361,000) 1,093,000 (495,600) 130,000 (60,000) 73,900 (33,500) 3,100 (1,400)	2,205 lb (1,000 kg) to polar 559 mile (900 km) orbit. Might be adapted for GO missions.
ISRAEL
Shavit 1988	N/A	1 2 3	Solid Solid Solid	N/A N/A N/A	Very little data available; derived from Jerico 2 missle. Launched Offeq 1, mass 344 lb (156 kg), into a 143 deg 155-715 mile (250-1,150 km) retrograde orbit.
JAPAN
Lambda-4S 1970	20,905 (9,480)	0 1 2 3 4	Solid Solid Solid Solid Solid	42,777 (19,400) 81,585 (37,000) 26,460 (12,000) 15,435 (7,000) 1,764 (800)	First Japanese satellite launcher. Launched Ohsumi, etc. Payload into CEO 53 lb (24 kg).
Mu-4S 1971	96,140 (43,600)	0 1 2 3 4	Solid Solid Solid Solid Solid	174,635 (79,200) 161,850 (73,400) 62,840 (28,500) 27,340 (12,400) 4,190 (1,900)	Launched Tansei 1, etc. Payload into CEO 507 lb (230 kg).
Mu-3C 1974	91,730 (41,600)	0 1 2 3	Solid Solid Solid Solid	171,110 (77,600) 165,375 (75,000) 62,620 (28,400) 12,790 (5,800)	Launched Tansei 2, etc. Payload into CEO 430 lb (195 kg).
Mu-3H 1977	107,385 (48,700)	0 1 2 3	Solid Solid Solid Solid	171,110 (77,600) 214,545 (97,300) 62,620 (28,400) 12,790 (5,800)	Launched Tansei 3, etc. Payload into CEO 595 lb (270 kg).
Mu-3S-I 1981	107,825 (48,900)	0 1 2 3	Solid Solid Solid Solid	171,110 (77,600) 229,320 (104,000) 62,620 (28,400) 13,010 (5,900)	Launched Tansei 4, ASTRO-A, etc. Payload into CEO 573 lb (260 kg).
Mu-3S-II 1984	134,505 (61,000)	0 1 2 3	Solid Solid Solid Solid	67,060 (30,414) 252,000 (114,285) 116,775 (52,960) 26,550 (12,040)	Major uprating of Mu-3S. Payload into 124 mile (200 km) CO 1,544 lb (700 kg); into solar orbit 331 lb (150 kg).
N-I 1975	199,025 (90,260)	0 1 2 3	Solid LO2/RJ-1 N2O4/Aerozine 50 Solid	156,575 (71,000) 169,785 (77,000) 11,905 (5,400) 8,820 (4,000)	Based on license-built Thor. Launched Kiku, etc. Payload into 186 mile (300 km) CO 2,646 lb (1,200 kg); into GO 287 lb (130 kg).
N-II 1981	297,675 (135,000)	0 1 2 3	Solid LO2/RJ-1 N2O4/Aerozine 50 Solid	470,325 (213,300) 169,785 (77,000) 9,700 (4,400) 14,995 (6,800)	Launched ETS-4, etc. Payload into GO 772 lb (350 kg).
H-I 1986	308,400 (139,900)	0 1 2 3	Solid LO2/RJ-1 LO2/LH2 Solid	331,000 (150,000?) 194,000 (88,000) 23,150 (10,500) 17,400 (7,900)	Derived from the N-I/N-II vehicles; four successful flights during 1986-88 with five further flights in 1989-92. 1,215 lb (550 kg) to GTO.
H-II 1994	586,400 (266,000)	0 1 2	Solid LO2/LH2 LO2/LH2	749,600 (340,000?) 264,600 (120,000) 26,500 (12,000)	Large booster under development in same class as Ariane 5 and Proton. 22,000 lb (10,000 kg) to 30 deg 186 miles (300 km), 8,800 lb (4,000 kg) to GTO.
UNITED KINGDOM
Black Arrow 1969	40,000 (18,140)	1 2 3	HTP/Kerosene HTP/Kerosene Solid	52,075 (23,615) 15,750 (7,145) 4,927 (2,235)	Launched X-3 Prospero 145.5 lb (66 kg). Payload into low PO 242 lb (110 kg). Project cancelled 1971.
UNITED STATES
Athena 1 1995	146,260 (66,345)	1 2	Solid Solid	400,000 (181,400) 43,250 (19,620)	Formerly LMLV 1.
Athena 2 1998	264,880 (120,150)	1 2 3	Solid Solid Solid	400,000 (181,400) 361,000 (163,700) 43,250 (19,620)	Formerly LMLV 2.
Atlas (Score) 1958	244,000 (110,660)	0 1	LO2/RP-1 LO2/RP-1	330,000 (149,660) 59,000 (26,755)	Launched Score active communications experiment.
Atlas-Able 1959	260,000 (117,915)	0 1 2 3	LO2/RP-1 LO2/RP-1 IWFNA/UDMH Solid	330,000 (149,660) 59,000 (26,755) 7,500 (3,400) 3,100 (1,405)	Derived from Atlas D ICBM plus Able stages from Vanguard launcher. Launched early Pioneer spacecraft, all three were failures.
Atlas-Agena A 1960	273,000 (123,810)	0 1 2	LO2/RP-1 LO2/RP-1 IRFNA/UDMH	330,000 (149,660) 59,000 (26,755) 10,110 (4,585)	Used in both Midas and Samos programs.
Atlas-Agena B 1961	275,000 (124,715)	0 1 2	LO2/RP-1 LO2/RP-1 IRFNA/UDMH	330,000 (149,660) 59,000 (26,755) 15,000 (6,800)	Various programs including Midas and Ranger. Payload into 300 mile (483 km) CO 5,000 lb (2,268 kg).
Atlas-Agena D 1963	274,965 (124,700)	0 1 2	LO2/RP-1 LO2/RP-1 IRFNA/UDMH	330,000 (149,660) 59,000 (26,755) 16,000 (7,255)	Various civil and military programs; reconnaissance and surveillance; Mariner 4, 5, Ranger 7, Lunar Orbiter, GETV, ATDA, etc.
Atlas-Burner 2 1968	286,440 (129,905)	0 1 2	LO2/RP-1 LO2/RP-1 Solid	370,000 (167,800) 59,000 (26,755) 8,800 (3,990)	Launched DSMP payloads, STP72-1 Radcat, etc. Burner 2A used post-1971; for data on that vehicle see Thor-Burner 2A.
Atlas-Centaur 1962	300,000+ (136,055+)	0 1 2	LO2/RP-1 LO2/RP-1 LO2/LH2	367,000 (166,440) 59,000 (26,755) 30,000 (13,605)	Originally designed to launch Advent comsat inot GO. Later developed to launch Surveyor lunar soft-landing spacecraft.
Atlas F 1977	262,500 (119,050)	0 1 2	LO2/RP-1 LO2/RP-1 Solid	330,000 (149,660) 59,000 (26,755) 14,330 (6,500)	Modified Atlas ICBM (1961). Launched Navstar, NOAA-7, Tiros-N, military payloads. Payload into 342 mile (560 km) orbit 3,307 lb (1,500 kg).
Atlas I 1990	361,300 (163,900)	1 2	LO2/RP-1 LO2/LH2	437,800 (198,600) 33,100 (15,000)	First of the new commercial Atlas series. 13,000 lb (5,900 kg) to LEO, 5,160 lb (2,340 kg) to GTO, and 3,350 lb (1,520 kg) to escape.
Atlas II 1991	412,600 (187,170)	1 2	LO2/RP-1 LO2/LH2	468,300 (212,400) 33,500 (15,200)	14,950 lb (6,780 kg) to LEO, 6,100 lb (2,770 kg) to GTO, and 4,280 lb (1,940 kg) to escape.
Atlas IIA 1992	412,900 (187,310)	1 2	LO2/RP-1 LO2/LH2	468,000 (212,300) 40,600 (18,400)	15,700 lb (7,120 kg) to LEO, 6,390 lb (2,900 kg) to GTO, and 4,630 lb (2,100 kg) to escape.
Atlas IIAS 1993	524,850 (238,070)	0 1 2	Solid LO2/RP-1 LO2/LH2	390,000 (176,900) 476,600 (216,200) 44,600 (20,230)	19,000 lb (8,618 kg) to LEO and 8,200 lb (3,719 kg) to GTO.
Atlas IIIA 2000	489,840 (222,190)	1 2	LO2/RP-1 LO2/LH2	860,400 (390,300) 22,300 (10,115)	19,150 lb (8,686 kg) to LEO and 8,950 lb (4,060 kg) to GTO.
Atlas IIIB 2002	500,270 (226,920)	1 2	LO2/RP-1 LO2/LH2	860,400 (390,300) 44,600 (20,230)	23,720 lb (10,759 kg) to LEO and 9,920 lb (4,500 kg) to GTO.
Atlas V 401 2002	739,810 (335,575)	1 2	LO2/RP-1 LO2/LH2	860,400 (390,300) 22,300 (10,115)	10,913 lb (4,950 kg) to GTO.
Atlas V 521 2003	953,440 (432,478)	0 1 2	Solid LO2/RP-1 LO2/LH2	510,810 (231,700) 860,400 (390,300) 22,300 (10,115)	13,856 lb (6,285 kg) to GTO.
Delta B DSV-3B 1962	114,170 (51,780)	1 2 3	LO2/RJ-1 IRFNA/UDMH Solid	172,000 (78,005) 7,575 (3,435) 2,760 (1,250)	Launched Relay 1, Syncom 1, Explorer 17, Telstar 2, etc. Payload into 300 mile (483 km) orbit 500 lb (227 kg).
Delta D DSV-3D 1964	143,325 (65,000)	0 1 2 3	Solid LO2/RJ-1 IRFNA/UDMH Solid	156,775 (71,100) 175,075 (79,400) 7,715 (3,500) 2,755 (1,250)	Launched Syncom 2, Early Bird. Payload into GO 230 lb (104 kg).
Delta E DSV-3E 1965	149,940 (68,000)	0 1 2 3	Solid LO2/RJ-1 IRFNA/UDMH Solid	156,775 (71,100) 175,075 (79,400) 7,805 (3,540) 2,755 (1,250)	Launched Explorer 29, Pioneer 6, ESSA 2,3,4,5, etc. Payload into GTO 441 lb (200 kg).
Delta 1000 Config. 1913 1972	295,470 (134,000)	0 1 2 3	Solid LO2/RJ-1 N2O4/Aerozine 50 Solid	470,325 (213,300) 175,075 (79,400) 9,810 (4,450) 9,505 (4,310)	This series introduced the "Straight Eight" Deltas. Config. 1913 launched Explorer 49, etc.
Delta 2000 Config. 2914 1974	293,100 (132,925)	0 1 2 3	Solid LO2/RJ-1 N2O4/Aerozine 50 Solid	470,325 (213,300) 205,065 (93,000) 9,810 (4,450) 14,995 (6,800)	Launced SMS, Westar, Anik, etc. Payload into GTO 1,550 lb (703 kg).
Delta 3914 1975	420,269 (190,560)	0 1 2 3	Solid LO2/RP-1 N2O4/Aerozine 50 Solid	766,015 (347,400) 205,065 (93,000) 9,810 (4,450) 14,995 (6,800)	Launched Satcom 1, etc. Payload into GTO 2,050 lb (030 kg).
Delta 3910 1980	418,000 (189,570)	0 1 2	Solid LO2/RP-1 N2O4/Aerozine 50	766,015 (347,400) 205,065 (93,000) 9,810 (4,450)	Launched SMM. Payload into low CO 5,500 lb (2,494 kg); into SSPO 2,985 lb (1,354 kg).
Delta 3920/PAM 1982	426,000 (193,200)	0 1 2 3	Solid LO2/RP-1 N2O4/Aerozine 50 Solid	766,015 (347,400) 205,065 (93,000) 9,810 (4,450) 18,500 (8,390)	Launched Landsat 4, Anik D, etc. Upgraded 3910 with improved 2nd stage injector and larger tanks. Payload into GTO 2,750 lb (1,247 kg).
Delta II 6920 1989	477,500 (216,600)	0 1 2	Solid LO2/RP-1 N2O4/Aerozine 50	978,200 (443,700) 231,700 (105,100) 9,700 (4,400)	8,781 lb (3,983 kg) to 28.7 deg 115 miles (185 km), 6,669 lb (3,025 kg) to 90 deg 115 miles (185 km), 5,659 lb (2,567 kg) to 98.7 deg 518 miles (833 km). Can also use PAMs for GO missions.
Delta II 7920 1990	502,900 (228,100)	0 1 2	Solid LO2/RP-1 N2O4/Aerozine 50	998,000 (452,700) 237,000 (107,500) 9,700 (4,400)	11,109 lb (5,039 kg) to 28.7 deg 115 miles (185 km), 8,419 lb (3,819 kg) to 90 deg 115 miles (185 km), 7,000 lb (3,175 kg) to 98.7 deg 518 miles (833 km). Can also use PAMs for GO missions.
Delta III 1998	664,580 (301,450)	0 1 2	Solid LO2/RP-1 LO2/LH2	1,230,300 (558,060) 244,100 (110,720) 24,750 (11,230)	18,280 lb (8,290 kg) to 28.7 deg 115 miles (185 km), 14,920 lb (6,770 kg) to 90 deg 124 miles (200 km), 13,450 lb (6,100 kg) to 98.6 deg 497 miles (800 km), and 8,400 lb (3,810 kg) to GTO.
Delta IV Medium 2003	550,000 (249,500)	1 2	LO2/LH2 LO2/LH2	650,000 (294,840) 24,750 (11,230)	20,075 lb (9,106 kg) to to 28.7 deg 253 miles (407 km), 9,327 lb (4,231 kg) to GTO, 6,905 lb (3,132 kg) to Moon, and 5,173 lb (2,347 kg) to Mars.
Delta IV Medium+ 4,2 2002	645,350 (292,730)	0 1 2	Solid LO2/LH2 LO2/LH2	273,400 (124,000) 650,000 (294,840) 24,750 (11,230)	27,116 lb (12,300 kg) to to 28.7 deg 253 miles (407 km), 13,098 lb (5,941 kg) to GTO, 9,798 lb (4,445 kg) to Moon, and 7,640 lb (3,465 kg) to Mars.
Delta IV Heavy 2004	1,618,000 (733,400)	0 1 2	LO2/LH2 LO2/LH2 LO2/LH2	1,300,000 (589,680) 650,000 (294,840) 24,750 (11,230)	48,264 lb (21,892 kg) to to 28.7 deg 253 miles (407 km), 28,124 lb (12,757 kg) to GTO, 21,949 lb (9,956 kg) to Moon, and 17,648 lb (8,005 kg) to Mars.
Gemini-Titan II 1964	340,000 (154,200)	1 2	N2O4/Aerozine 50 N2O4/Aerozine 50	430,000 (195,010) 100,000 (45,350)	Modified ICBM. Launched Gemini two-man spacecraft into CEO.
Juno I 1958	64,000 (29,025)	1 2 3 4	LO2/Hydyne Solid Solid Solid	83,000 (37,640) 16,500 (7,485) 5,400 (2,450) 1,800 (816)	Derived from Jupiter C (started under NRL "Orbiter" Project). Launched Explorer 1, 3 and 4.
Juno II 1958	122,000 (55,330)	1 2 3 4	LO2/RP-1 Solid Solid Solid	150,000 (68,025) 16,500 (7,485) 5,400 (2,450) 1,800 (816)	Derived from Jupiter IRBM and Jupiter C upper stages. Launched Pioneer 3 & 4, etc. Payload into 300 mile (483 km) orbit 100 lb (45 kg).
Mercury-Redstone 1961	66,000 (29,930)	1	LO2/Ethanol+Water	78,000 (35,375)	Derived from Redstone MRBM. Launched Shepard and Grissom.
Mercury-Atlas 1962	260,000 (117,915)	0 1	LO2/RP-1 LO2/RP-1	367,000 (166,440) 59,000 (26,755)	Derived from Atlas D ICBM. Launched first U.S. astronaunts into Earth orbit.
Pegasus/B-52 1989	40,600 (18,400)	1 2 3	Solid Solid Solid	112,000 (50,800) 28,000 (12,700) 9,000 (4,100)	Carried to altitude by B-52 and then separates and continues to orbit. 595 lb (270 kg) to polar 286 mile (460 km) orbit.
Saturn I 1961	1,122,000 (508,845)	1 2	LO2/RP-1 LO2/LH2	1,504,000 (682,085) 90,000 (40,815)	Used for R&D. Data relate to SA-5 which put 37,900 lb (17,190 kg) into EO.
Saturn IB 1966	1,295,000 (587,300)	1 2	LO2/RP-1 LO2/LH2	1,640,000 (743,765) 225,000 (102,040)	Launched Apollo 7, Skylab and ASTP astronaunts. 40,000 lb (18,140 kg) to EO.
Saturn V/Apollo 1967	6,423,000 (2,912,925)	1 2 3	LO2/RP-1 LO2/LH2 LO2/LH2	7,650,000 (3,469,390) 1,150,000 (521,540) 238,000 (107,935)	Launched Apollo astronaunts to the Moon.
Saturn V/Skylab 1973	6,222,000 (2,821,770)	1 2	LO2/RP-1 LO2/LH2	7,723,726 (3,502,820) 1,125,000 (510,205)	Launched Skylab space station into Earth orbit.
Scout 1960	36,600 (16,600)	1 2 3 4	Solid Solid Solid Solid	115,000 (52,155) 50,000 (22,675) 13,600 (6,170) 3,000 (1,360)	Launched Explorer 9 & 13, etc. Payload into 300 mile (483 km) CO 150 lb (68 kg).
Scout D 1972	47,000 (21,315)	1 2 3 4	Solid Solid Solid Solid	108,300 (49,115) 63,200 (28,660) 28,500 (12,925) 5,900 (2,675)	Launched Meteoroid Technology Satellite, SAS-B, UK-6, etc. Payload into 300 mile (483 km) CO 390 lb (177 kg).
Space Shuttle 1981	4,500,000 (2,040,815)	0 1	Solid LO2/LH2 + N2O4/MMH	5,300,000 (2,403,630) 1,410,000 (639,455) 12,000 (5,440)	Max payload into CEO, due East launch Cape Canaveral, 65,000 lb (29,478 kg). First flight (STS-1) 12-Apr-81.
Thor-Able 1958	114,660 (52,000)	1 2 3	LO2/RJ-1 IRFNA/UDMH Solid	150,000 (68,025) 7,575 (3,435) 2,760 (1,250)	Launched first Pioneer Moon probes. Derived from Thor IRBM with modified Vanguard second stage.
Thor-Able Star 1960	117,900 (53,470)	1 2	LO2/RJ-1 IRFNA/UDMH	172,000 (78,005) 7,730 (3,505)	Launched Transit, Courier, etc. Payload into 300 mile (483 km) CO 1,000 lb (454 kg).
Thor-Agena A 1959	117,000 (53,060)	1 2	LO2/RJ-1 IRFNA/UDMH	150,000 (68,025) 15,500 (7,030)	Launched early Discoverers. Payload into 300 mile (483 km) CO 300 lb (136 kg).
Thor-Agena B 1960	123,040 (55,800)	1 2	LO2/RJ-1 IRFNA/UDMH	172,000 (78,025) 16,000 (7,255)	Discoverer series. Payload into 300 mile (483 km) CO 1,600 lb (726 kg).
Thor-Agena D 1962	123,040 (55,800)	1 2	LO2/RJ-1 IRFNA/UDMH	172,000 (78,025) 16,000 (7,255)	Various military and civil programs.
Thor-Burner 2A 1971	N/A	1 2 3	LO2/RJ-1 Solid Solid	172,000 (78,005) 10,000 (4,535) 8,800 (3,990)	Launched DMSP. Thor-Burner 1 used an Altair motor. Thor-Burner 2 omitted the third stage.
Titan 2G 1988	345,000 (156,500)	1 2	N2O4/Aerozine 50 N2O4/Aerozine 50	430,000 (195,000) 100,000 (45,350)	Titan missle adapted for satellite launch vehicle. 4,850 lb (2,200 kg) to polar 115 mile (185 km) orbit.
Titan IIIA 1964	407,925 (185,000)	1 2 3	N2O4/Aerozine 50 N2O4/Aerozine 50 N2O4/Aerozine 50	430,000 (195,000) 100,000 (45,350) 16,000 (7,255)	Launched LES-1,2, radar calibration satellite. Payload into 100 mile (161 km) EO 3,300 lb (1,497 kg).
Titan IIIB-Agena 1966	454,450 (206,100)	1 2 3	N2O4/Aerozine 50 N2O4/Aerozine 50 IRFNA/UDMH	463,200 (210,070) 101,000 (45,805) 16,800 (7,620)	Launched various payloads. Payload into 100 mile (161 km) EO 8,550 lb (3,877 kg).
Titan IIIC 1965	1,392,000 (631,290)	0 1 2 3	Solid N2O4/Aerozine 50 N2O4/Aerozine 50 N2O4/Aerozine 50	2,360,000 (1,070,295) 532,000 (241,270) 101,000 (45,805) 16,000 (7,255)	Launched IDCSP, Vela, DSCS, ATS-6, etc. Payload into 100 mile (161 km) EO 29,600 lb (13,425 kg); into GO 3,600 lb (1,633 kg).
Titan IIID 1971	1,300,000 (589,570)	0 1 2	Solid N2O4/Aerozine 50 N2O4/Aerozine 50	2,360,000 (1,070,295) 532,000 (241,270) 101,000 (45,805)	Launched "Big Bird", KH-11, etc. Payload into PO 13,000 lb (5,895 kg).
Titan IIIE-Centaur 1974	1,411,200 (640,000)	0 1 2 3	Solid N2O4/Aerozine 50 N2O4/Aerozine 50 LO2/LH2	2,361,000 (1,070,750) 530,000 (240,360) 101,000 (45,805) 30,000 (13,605)	Launched Helios, Viking, Voyager, etc. Payload into GO 7,400 lb (3,356 kg); to Venus or Mars 8,400 lb (3,809 kg); to outer planets 500-1,750 lb (227-749 kg).
Titan 34D 1982	1,724,530 (782,100)	0 1 2 3 4	Solid N2O4/Aerozine 50 N2O4/Aerozine 50 Solid Solid	2,498,000 (1,132,880) 532,000 (241,270) 101,000 (45,805) 62,000 (28,120) 26,000 (11,790)	Launched DSCS 2 and other military missions. Payload into 100 mile (161 km) EO 27,500 lb (12,470 kg); into GO 4,200 lb (1,905 kg).
Titan III (Commercial) 1990	1,500,000 (680,000)	0 1 2	Solid N2O4/Aerozine 50 N2O4/Aerozine 50	2,792,000 (1,266,600) 1,092,200 (495,400) 104,100 (47,200)	Latest Titan III variant. Can carry two payloads totalling 31,600 lb (14,334 kg) or a single payload of 32,500 lb (14,742 kg) to 28.6 deg, 92-161 mile (148-259 km) orbit. Can also carry IUS or PAMs with payloads for GTO/GSO missions.
Titan III-T 1992	1,532,000 (695,000)	0 1 2 3	Solid N2O4/Aerozine 50 N2O4/Aerozine 50 N2O4/Aerozine 50	2,792,000 (1,266,600) 1,092,200 (495,400) 104,100 (47,200) 32,200 (14,600)	Titan III plus Transtage. Can place single 10,200 lb (4,626 kg) payload or two payloads totalling 9,500 lb (4,309 kg) into GTO or 2,100 lb (952 kg) into GSO.
Titan IV 1989	1,760,000 (800,000)	0 1 2	Solid N2O4/Aerozine 50 N2O4/Aerozine 50	3,567,000 (1,618,000) 1,100,000 (498,000) 106,000 (48,000)	Growth version of Titan 34D. 39,000 lb (17,700 kg) to 28.6 deg LEO or 32,000 lb (14,500 kg) to polar LEO. Can fly GTO/GSO or escape missions using Centaur or IUS.
Vanguard 1958	22,600 (10,250)	1 2 3	LO2/Kerosene IWFNA/UDMH Solid	28,000 (12,700) 7,500 (3,400) 3,100 (1,405)	First orbital attempt (TV3) failed. TV4 launched Vanguard 1 test satellite.
SOVIET UNION - RUSSIA - UKRAINE
A (SL-1) 1957	588,735 (267,000)	0 1	LO2/Kerosene LO2/Kerosene	877,590 (398,000) 205,065 (93,000)	Derived from R.7 ICBM, SS-6 Sapwood. Launched Sputniks 1, 2 and 3. Dry weight 48,510 lb (22,000 kg).
A-1 (SL-3) 1959	615,195 (279,000)	0 1 2	LO2/Kerosene LO2/Kerosene LO2/Kerosene	899,500 (408,000) 211,600 (96,000) 11,025 (5,000)	Launched Luna 1, 2 and 3. Additional Luna payloads were launched but went off course. Dry weight 52,920 lb (24,000 kg).
A-1 (SL-3, Vostok) 1959	639,300 (290,000)	0 1 2	LO2/Kerosene LO2/Kerosene LO2/Kerosene	899,500 (408,000) 211,000 (96,000) 12,300 (5,600)	Carried first man into space (1961), now rarely used for SSO missions. 11,000 lb (5,000 kg) to LEO, 4,050 lb (1,840 kg) to 98 deg 404 miles (650 km), 2,540 lb (1,150 kg) to 99 deg 572 miles (920 km).
A-2 (SL-4, Soyuz) 1963	676,800 (307,000)	0 1 2	LO2/Kerosene LO2/Kerosene LO2/Kerosene	899,500 (408,000) 211,600 (96,000) 66,100 (30,000)	Carries manned Soyuz, Soyuz-T, Soyuz-TM craft and Progress ferries, as well as reconnaissance satellites. 16,500 lb (7,500 kg) to 51.6 deg 124 miles (200 km), 15,200 lb (6,900 kg) to 50.5 deg 124-280 miles (200-450 km).
A-2-e (SL-6 Molniya) 1960	679,000 (308,000)	0 1 2 3	LO2/Kerosene LO2/Kerosene LO2/Kerosene LO2/Kerosene	899,500 (408,000) 211,600 (96,000) 66,100 (30,000) 14,800 (6,700)	Molniya and early warning missions. 4,400 lb (2,000 kg) to 63 deg 310-24,200 miles (500-39,000 km), 3,750 lb (1,700 kg) to the Moon, 2,760 lb (1,250 kg) to Mars or Venus.
B-1 (SL-7) 1962	94,815 (43,000)	1 2	IRFNA/Kerosene LO2/UDMH	158,760 (72,000) 24,255 (11,000)	Derived from SS-4 Sandal MRBM. Launched Cosmos and Intercosmos family.
C-1 (SL-8, Cosmos) 1964	275,600 (125,000)	1 2	Nitric Acid/UDMH N2O4/UDMH	388,000 (176,000) 33,000 (15,000)	First stage derived from SS-5/Skean. 2,800 lb (1,250 kg) to LEO from Kapustin Yar, 1,800 lb (810 kg) to 83 deg 620 miles (1,000 km) from Plesetsk.
D (SL-9) 1965	1,313,000 (595,500)	1 2	N2O4/UDMH N2O4/UDMH	2,355,000 (1,068,000) 529,000 (240,000)	Launched Proton 1, 2 and 3, all 26,900 lb (12,200 kg). Rumored launch failure in early 1966.
D-1 (SL-13, Proton 3-stage variant) 1968	1,540,000 (700,000)	1 2 3	N2O4/UDMH N2O4/UDMH N2O4/UDMH	2,355,000 (1,068,000) 529,000 (240,000) 141,000 (64,000)	Two stage Proton flew four times during 1965-1966 (one failure). Three stage variant used for Salyut series, 41,700-43,920 lb (18,900-19,920 kg), Mir core 46,100 lb (20,900 kg) and Mir modules 45,400 lb (20,600 lb) to 51.6 deg 130-155 miles (210-250 km).
D-1-e (SL-12, Proton 4-stage variant) 1967	1,540,000 (700,000)	1 2 3 4	N2O4/UDMH N2O4/UDMH N2O4/UDMH LO2/Kerosene	2,355,000 (1,068,000) 529,000 (240,000) 141,000 (64,000) 19,200 (8,700)	Three stage Proton with fourth stage (Block-D, now Block-DM) added. 4,675 lb (2,120 kg) to GTO, 10,250 lb (4,650 kg) to Mars, 11,685 lb (5,300 kg) to Venus and 12,630 lb (5,730 kg) to the Moon.
F-1-r, F-1-m (SL-11, Tsyklon 2-stage variant) 1966	400,000 (180,000)	1 2	N2O4/UDMH N2O4/UDMH	617,000 (280,000) 198,400 (90,000)	Ocean surveillance, ASAT and FOBS missions. 8,800 lb (4,000 kg) to 65 deg 155-165 miles (250-265 km).
F-2 (SL-14, Tsyklon 3-stage variant) 1977	440,000 (200,000)	1 2 3	N2O4/UDMH N2O4/UDMH N2O4/UDMH	617,000 (280,000) 198,400 (90,000) 17,900 (8,100)	Meteorological, oceanographic and minor military payloads. 8,800 (4,000 kg) to LEO, 2,870 lb (1,300 kg) to 82.6 deg 746 miles (1,200 km).
G-1-e (SL-15, Soviet name N-1) 1969	5,914,200 (2,682,650)	1 2 3 4	LO2/Kerosene LO2/Kerosene LO2/Kerosene LO2/Kerosene	9,733,000 (4,415,000) 3,156,000 (1,432,000) 362,000 (164,000) 100,000 (45,500)	Super-booster for manned lunar flight. Launch failures 21-Feb and 3-Jul-69; 2 more failures 27-Jun-71 and 23-Nov-72. Three stages to Earth orbit, plus a fourth escape stage.
J-1 (SL-16, Zenit) 1985	1,014,000 (460,000)	1 2	LO2/Kerosene LO2/Kerosene	1,779,000 (807,000) 205,000 (93,000)	Medium lift launch vehicle; 30,290 lb (13,740 kg) to 51.6 deg 124 mile (200 km) orbit from Baikonur.
K-1 (SL-17, Energiya) 1987	5,290,000 (2,400,000)	0 1	LO2/Kerosene LO2/LH2	7,108,000 (3,224,000) 1,764,000 (800,000)	Heavy lift launch vehicle, first flown 15-May-87. Can theoretically place 309,000 lb (140,000 kg) into 51.6 deg 152-158 mile (245-255 km) orbit.
K-1 (Energiya, 3-stage variant)	4,630,000 (2,100,000)	0 1 2	LO2/Kerosene LO2/LH2 LO2/Kerosene	7,108,000 (3,224,000) 1,764,000 (800,000) 441,000 (200,000)	39,700 lb (18,000 kg) to GTO, 61,700 lb (28,000 kg) to Mars and Venus, 70,500 lb (32,000 kg) to the Moon.
K-1 (Energiya, 2 strap-on variant)	3,836,000 (1,740,000)	0 1	LO2/Kerosene LO2/LH2	3,554,000 (1,612,000) 1,764,000 (800,000)	Standard Energiya, but with only two strap-on boosters; 143,300 lb (65,000 kg) to 51.6 deg 124 mile (200 km) orbit.
K-1/VKK (SL-17, Energiya/Shuttle) 1988	4,630,000 (2,100,000)	0 1	LO2/Kerosene LO2/LH2	7,108,000 (3,224,000) 1,764,000 (800,000)	First flight with Buran shuttle orbiter 15-Nov-88. Orbiter maximum mass 231,500 lb (105,000 kg); payload 66,100 lb (30,000 kg) to 51.6 deg 155 miles (250 km).

Compiled and edited by Robert A. Braeunig, 1996, 2005.
Bibliography

http://www.braeunig.us/space/index.htm

Penulis : Drts.Simon  Arnold Julian Jacob