| Rocket: | Thrust/ Stages (lb) | Fuel/ Stages (lb) | Length (ft) | Diameter (ft) | Weight (lb) | Designer |
| Algol | 104,500 | Solid | 29.8 | 3.3 | 22,460 | US |
| Altair | 3,060 | Solid | 4.8 | 1.5 | 514 | US |
| Antares | 14,500 | Solid | 9.6 | 2.5 | 2,300 | US |
| Asp | 6,000 | Solid | 8.9 | 0.5 | 192 | US |
| Atlas (Score) | 330,000 59,000 |
LO2/RP-1 LO2/RP-1 |
85.0 | 10
(upper) 16 (lower) |
244,000 | US (1958) |
| Atlas-Able | 330,00059,0007,5003,100 | LO2/RP-1LO2/RP-1IWFNA/UDMHSolid | 98.0 | 1016 | 260,000 | US (1959) |
| Atlas-Agena A | 330,00059,00015,000 | LO2/RP-1LO2/RP-1IRFNA/UDMH | 99.0 | 1016 | 273,000 | USAF (1960) |
| Atlas-Agena B | 330,00059,00015,000 | LO2/RP-1LO2/RP-1IRFNA/UDMH | 98 | 1016 | 275,000 | USAF, NASA (1961) |
| (Mercury) Atlas | 367,000
59,000 |
LO2/RP-1
LO2/RP-1 |
95.3 | 10.0 | 260,000 | NASA, MSFC (1962) |
| Atlas-Agena D | 330,00059,00016,000 | LO2/RP-1LO2/RP-1IRFNA/UDMH | 102.0 | 1016 | 274,965 | USAF,
NASA (1963) |
| Atlas-Burner 2 | 370,00059,0008,800 | LO2/RP-1LO2/RP-1
Solid |
78.7 | 10
16 |
286,440 | USAF (1968) |
| Atlas-Centaur | 367,00059,00030,000 | LO2/RP-1LO2/RP-1LO2/LH2 | 105.0 | 1016 | 325,732 | US (1962) |
| Atlas-Centaur | 370,0061,30030,000 | LO2/RP-1LO2/RP-1LO2/LH2 | 131.0 | 1016 | 329,017 | NASA (1966) |
| Atlas F | 330,00059,00014,330 | LO2/RP-1LO2/RP-1Solid | 85.0 | 1016 | 262,500 | USAF, NASA (1977) |
| Black Arrow | 50,00015,350- | Hydrogen-
peroxide/
keroseneHydrogen-Peroxide/keroseneSolid |
43.1 | 6.5 | 40,000 | Great Britain |
| Cajun I | 8,100 | Solid | 9 | 0.6 | 172 | US |
| Castor | 55,000 | Solid | 20.3 | 2.6 | 8,870 | US |
| Delta
B
DSV-3B |
172,0007,5752,760 | LO2/RJ-1IRFNA/UDMHSolid | 87.9 | 8.0 | 114,170 | NASA (1962) |
| Delta
D
DSV-3d |
156,775175,0757,7152,755 | SolidLO2/RJ-1IRFNA/UDMH
Solid |
92.8 | 8.0 | 143,325 | NASA (1964) |
| Delta
E
DSV-3E |
156,775175,0757,8052,755 | SolidLO2/RJ-1IRFNA/UDMHSolid | 95.8 | 8.0 | 149,940 | NASA (1965) |
| Delta
(1000)
(1913) |
470,325175,0759,8109,505 | SolidLO2/RJ-1N2O4/Aerozine
50
Solid |
116.0 | 8.0 | 295,470 | NASA (1972) |
| Delta
2000
(2914) |
470,325205,0659,81014,995 | SolidLO2/RP-1N2O4/Aerozine 50Solid | 116.0 | 8.0 | 293,110 | NASA (1974) |
| Delta 3914 | 766,015205,0659,81014,995 | SolidLO2/RP-1N2O4/Aerozine 50Solid | 116.0 | 8.0 | 420,269 | NASA (1975) |
| Delta 3910 | 766,015205,0659,810 | SolidLO2/RP-1N2O4/Aerozine 50 | 116.0 | 8.0 | 418,000 | NASA
(1980) |
| Delta 3910/PAM | 766,015205,0659,81018,500 | SolidLO2/RP-1N2O4/Aerozine 50Solid | 116.0 | 8.0 | 422,100 | NASA
(1980) |
| Delta 3920/PAM | 766,015205,0659,81018,500 | SolidLO2/RP-1N2O4/Aerozine 50Solid | 116.0 | 8.0 | 426,000 | NASA
(1982) |
| Diamant B | 78,50033,80011,500 | Nitrogen tetroxide-UDMHSolidSolid | 78.4 | 4.05 | 53,800 | France |
| Dolphin | 42,000 | Hybrid:Polybuladyne rubber/LO2 | 51.0 | 3.5 | 18,000 | US (1984) |
| Europa 1 | 300,00060,0005,000 | LOX-keroseneNitrogen teroxide-UDMHNitrogen tetroxide-hydrazine and UDMH mixture | 92 | 10 | 230,500 | European
Consortium |
| Juno 1 | 83,000
16,500 5,400 1,800 |
LO2/'Hydyne'
Solid Solid Solid |
71.25 | 5.8 | 64,000 | NASA, MFSC (1958) |
| Juno 2 | 150,00016,5005,4001,800 | LO2/RP-1Solid
Solid Solid |
76.6 | 8.75 | 122,000 | NASA, MFSC (1958) |
| Lance | 38,800 | Solid | 15.4 | 1.3 | 1,682 | US |
| Mercury-
Redstone |
78,000 | LO2/eythl
alcohol +
water |
83.0 | 5.8 | 66,000 | NASA, MFSC (1961) |
| Meteor | 2,600 | Solid | 4.8 | 1.5 | 431 | US |
| Nike Booster | 50,000 | Solid | 12.5 | 1.3 | 1.170 | US |
| Recruit | 35,000 | Solid | 8.9 | 0.8 | 350 | US |
| Saturn 1 | 1,504,000
90,000 |
LO2/RP-1
LO2/LH2 |
164.0 | 21.5 | 1,122,000 | NASA
(1961) |
| Saturn 1B | 1,640,000225,000 | LO2/RP-1
LO2/LH2 |
224.0 | 21.7 | 1,295,000 | NASA, MFSC (1966) |
| Saturn
5/
Apollo |
7,650,0001,150,000238,000 | LO2/RP-1
LO2/LH2 LO2/LH2 |
363.0 | 33.0 | 6,423,000 | NASA, MFSC (1967) |
| Saturn
5/
Skylab |
7,724,0001,125,000 | LO2/RP-1
LO2/LH2 |
333.7 | 33.0 | 6,222,000 | NASA, MFSC (1973) |
| Scout | 115,00050,00013,0003,000 | Solid
Solid Solid Solid |
72.0 | 3.3 | 36,600 | NASA (1960) |
| Scout D | 108,000
63,000 28,500 5,900 |
Solid
Solid Solid Solid |
75.5 | 3.8 | 47,000 | NASA, USAF (1972) |
| Space Shuttle | 5,3000,0001,410,00012,000 | Solid
LO2/LH2 N2O4/MMH |
184.2
122.2 |
78.1 (wing span) | 4,500,000 | NASA, USAF (1981) |
| Thor-Able | 5,300,0001,410,000
12,000 |
LO2/RJ-1
IRFNA/UDMH Solid |
90.0 | 8.0 | 114,660 | NASA, USAF (1958) |
| Thor-Able Star | 172,0007,730 | LO2/RJ-1
IR (or W) FNA/UDMH |
79.3 | 8.0 | 117,900 | USAF (1960) |
| Thor-Agena A | 150,00015,500 | LO2/RJ-1
IRFNA/UDMA |
78.5 | 8.0 | 117,000 | USAF (1959) |
| Thor-Agena
B |
172,00016,000 | LO2/RJ-1
IR (or W) FNA/UDMH |
81.3 | 8.0 | 123,040 | USAF (1960) |
| Thor-Agena D | 172,00016,000 | LO2/RJ-1
FNA/UDMH |
76.3 | 8.0 | 123.040 | USAF, NASA (1962) |
| Thor-Burner 2A | 172,00010,000av8,800 | LO2/RJ-1
Solid Solid |
85.0 | 8.0 | N/A | USAF (1971) |
| Titan IIIA | 430,000100,00016,000 | N2O4/
Aerozine 50
N2O4/ Aerozine 50 N2O4/ Aerozine 50 |
108.0 | 10.0 | 407,925 | USAF (1964) |
| (Gemini) Titan II | 430,000100,,000 | N2O4/
Aerozine 50
N2O4/ Aerozine 50 |
109.0 | 10.0 | 407,925 | NASA
(1964) |
| Titan IIIB-Agena | 463,200101,00016,800 | N2O4/
Aerozine 50
N2O4/ Aerozine 50 IRFNA/UDMH |
160.0 max | 10.0 | 454,450 | USAF
(1966) |
| Titan IIIC | 2,360,000532,000101,00016,000 | Solid
N2O4/ Aerozine 50 N2O4/ Aerozine 50 N2O4/ Aerozine 50 |
157.0 max | 10.0 | 1,392,000 | USAF, NASA (1965) |
| Titan IIID | 2,360,000532,000101,000 | Solid
N2O4/ Aerozine 50 N2O4/ Aerozine 50 |
155.0 max | 10.0 | 1,300,000 | USAF,
NASA
(1971) |
| Titan
IIIE-
Centaur |
2,361,000530,000
101,000 30,000 |
Solid
N2O4/ Aerozine 50 N2O4/ Aerozine 50 LO2/LH2 |
160.0 | 10.0 | 1,411,200 | NASA (1974) |
| Titan 34D | 2,498,000530,000101,00062,00026,000 | Solid
N2O4/ Aerozine 50 N2O4/ Aerozine 50 Solid Solid |
160.7 max | 10.0 | 1,742,530 | NASA,
USAF
(1982) |
| Vanguard | 28,0007,5003,100 | LO2/
Kerosene IWFNA/UDMH Solid |
72.0 | 3.7 | 22,600 | US Navy (1958) |
Russian Rockets:
| Rocket | Thrust/ Stages (tonnes) | Fuel/ Stages | Length (metres) | Diameter (metres) | Weight (tonnes) |
| Cosmos SL-8 | 176 - - | Nitric
acid/UDMH
- - |
31.2 | 2.44
2.44 |
124.95 |
| Energiya SL-17 | 806200Not Known | LOX/
Kerosene
Not Known Not Known |
60 | 4
8 4 |
2654 |
| Energiya SL-? | 806200Not Known | LOX/
Kerosene
LOX/LH Not Known |
60 | 4
8 5.5 |
3576 |
| Proton SL-12 | 167240648.7 | Nitrogen
tetroxide/ UDMH
Nitrogen tetroxide/ UDMH Nitrogen tetroxide/ UDMH LOX/ Kerosene |
58.9 | 7.4
4.15 4.15 3.7 |
699.8 |
| Proton SL-13 | 16724064 | Nitrogen
tetroxide/ UDMH
Nitrogen tetroxide/ UDMH Nitrogen tetroxide/ UDMH |
59.8 | 7.4
4.15 4.15 |
697.1 |
| Soyuz SL-4 | 1029630 | LOX/Kerosene
LOX/Kerosene LOX/Kerosene |
49.3 | 2.68
2.95 2.66 |
309.53 |
| Vostok Sl-3 | 102965.6 | LOX/Kerosene
LOX/Kerosene LOX/Kerosene |
38.36 | 2.68
2.95 2.6 |
287.03 |
| Voskhod SL-4 | 1029630 | LOX/Kerosene
LOX/Kerosene LOX/Kerosene |
44.9 | 2.68
2.95 2.66 |
307.26 |
Abbreviations:
*UDMH - Unsymetrical dimethylhydrazine
*LOX or LO2 - Liquid oxygen
*LH2 - Liquid hydrogen
*H - Hydrogen
*FNA – Fuming nitric acid
*IRFNA - Inhibited red fuming nitric acid
*IWFNA - Inhibited white fuming nitric acid
*SL - Sattelite Launching
*MSFC - Marshall Space Flight Center
*NASA - National Aeronautics and Space Administration
*USAF - United States Air Force