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SPACE LAUNCH VEHICLES

SPACE LAUNCH VEHICLES



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

NAMEMASS
lb (kg)
SPROPELLANT 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)
1LO2/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

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