Comparison of solid-fuelled orbital launch systems
This page contains the lift launch systems constructed by some solid fuel stages except final stage.
All stages solid fueled
| Vehicle | Stage number | Origin | Manufacturer | Height (meter) | Diameter (meter) | Weight (ton) | Mass to LEO (kg) |
Mass to Other Orbit (kg) |
Maiden flight | Retired | Record | Status |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| ASLV | 5 |  India |
ISRO | 24 | 1 | 41 | 150 | 1987 | 1994 | 2/4 | Retired | |
| Epsilon (without PBS) |
3 |  Japan |
IHI AeroSpace | 24.4 | 2.6 | 90.8 | - | 0/0 | Active | |||
| J-I | 2(+1) | Japan |
NASDA / ISAS | 33.1 | 1.8 | 88.5 | 1000 | 1996 | 1996 | 1/1* | Retired | |
| Kaituozhe-1 |  China |
Space Solid Fuel Carrier Co. | SSO:50 kg ? | 2002 | - | 0/2 | Active | |||||
| Kuaizhou | ? | China |
? | ? | ? | ? | ? | ? | 2013 | - | 2/2 | Active |
| L-4S | 4 | Japan |
Tokyo univ. | 16.5 | 0.735 | 9.4 | 26 | 1966 | 1970 | 1/5 | Retired | |
| Minotaur I | 4 |  United States |
Orbital Sciences | 19.2 | 1.67 | 36.2 | 580 | SSO: 331 | 2000 | - | 11/11 | Active |
| Minotaur IV Lite | 3 | United States |
Orbital Sciences | 23.88 | 2.34 | 86.3 | - | 2010 | - | 2/2* | Active | |
| Minotaur IV | 4 | United States |
Orbital Sciences | 23.88 | 2.34 | 86.3 | 1735 | 2010 | - | 1/1 | Active | |
| Minotaur IV+ | 4 | United States |
Orbital Sciences | 23.88 | 2.34 | 86.3 | 1985 | 2011 | - | 1/1 | Active | |
| Minotaur V | 5 | United States |
Orbital Sciences | 1.67 | GTO:640 TLI:447 | 2013 | - | 1/1 | Active | |||
| M-3C | 3 | Japan |
Tokyo univ. | 20.2 | 1.41 | 41.8 | 195 | 1974 | 1979 | 3/4 | Retired | |
| M-3H | 3 | Japan |
Tokyo univ. | 23.8 | 1.41 | 48.7 | 300 | 1977 | 1978 | 3/3 | Retired | |
| M-3S | 3 | Japan |
Tokyo univ. | 23.8 | 1.41 | 48.7 | 300 | 1980 | 1984 | 4/4 | Retired | |
| M-3SII | 3(+1) | Japan |
ISAS | 27.8 | 1.41 | 61 | 770 | 1985 | 1995 | 7/8 | Retired | |
| M-4S | 4 | Japan |
Tokyo univ. | 23.6 | 1.41 | 43.6 | 180 | 1970 | 1972 | 3/4 | Retired | |
| M-V | 3(+1) | Japan |
ISAS | 30.8 | 2.5 | 140 | 1850 | Interplanetary: 500 | 1997 | 2006 | 6/7 | Retired |
| Pegasus | 3 | United States |
Orbital Sciences | 16.9 | 1.27 | 18.5 | 375 | 1990 | 10/11 | Active(?) | ||
| Pegasus XL | 3 | United States |
Orbital Sciences | 17.6 | 1.27 | 23.13 | 443 | 1994 | - | 28/31 | Active | |
| Scout | 4(?) | United States |
NACA | 23 | 1.01 | 21.5 | 1961 | 1994 | Retired | |||
| Scout-A | 4 | United States |
NACA | 25 | 1.01 | 17.85 | Retired | |||||
| Shavit | 3 |  Israel |
IAI | 15.3 | 1.352 | 23.2 | 160 | 1988 | 1990 | 2/2 | Retired | |
| Shavit1 (LK-A) | 3 | Israel |
IAI | 17.2 | 1.352 | 27.3 | 240 | 1995 | 2004 | 2/4 | Retired | |
| Shavit2 (LK-1) | 3 | Israel |
IAI | 19.5 | 1.352 | 31.2 | 350 | 2007 | - | 2/2 | Active | |
| SLV | 4 | India |
ISRO | 22 | 1 | 17 | 40 | 1979 | 1983 | 3/4 | Retired | |
| RPS-420 | 4 |  Indonesia |
LAPAN | 9.5 | 0.42 | 50 | (2014) | - | 0/0 | Development | ||
| SPARK (Super Strypi) |
3 | United States |
Hawaii, Sandia, Aerojet Rocketdyne |
SSO: 250 | 2015 | - | 0/1 | Active | ||||
| Start-1 | 4 |  Russia |
MIT | 22.7 | 1.61 | 47.2 | 532 | SSO: 167 | 1993 | - | 6/6 | Active |
| Taiwan SLV | 4 |  Republic of China |
NSPO | 50 | - | - | 0/0 | Development | ||||
| Taurus | 3+1 | United States |
Orbital Sciences | 27 | 2.35 | 69 | 1259 | SSO: 889 | 1994 | - | 5/6 | Active ? |
| Taurus XL | 3+1 | United States |
Orbital Sciences | 32 | 2.35 | 77 | 1458 | SSO: 1054 | 2004 | - | 1/3 | Active |
| VLS-1 | 3 |  Brazil |
AEB | 19.5 | 1.01 | 50.7 | 380 | 1997 | - | 0/2 | Development |
- * Including suborbital mission
Partial liquid fueled
| Vehicle | Main stages (S:solid / L:liquid) | Origin | Manufacturer | Height (meter) | Diameter (meter) | Weight (ton) | Mass to LEO (kg) |
Mass to Other Orbit (kg) |
Maiden flight | Retired | Record | Status |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Ares I | 1S+1L | United States |
Alliant Techsystems / Boeing | 94 | 5.5 | 25000 | (2015) | 0/0 | Development (to be cancelled) | |||
| Athena I | 2S+1L | United States |
Lockheed Martin | 1995 | 2001 | 3/4 | Retired | |||||
| Athena Ic | 2S+1L | United States |
Lockheed Martin Alliant Techsystems |
(2012) | 0/0 | Development | ||||||
| Athena II | 3S+1L | United States |
Lockheed Martin | 30.5 | 2.36 | 120.2 | 1896 | 1998 | 1999 | 2/3 | Retired | |
| Athena IIc | 3S+1L | United States |
Lockheed Martin Alliant Techsystems |
(2012) | 0/0 | Development | ||||||
| Epsilon PBS | 3S+1L | Japan |
IHI AeroSpace | 24.4 | 2.6 | 90.8 | 2013 | - | 1/1 | Active | ||
| Long March 11 | 3S+1L | China |
2015 | 1/1 | Active | |||||||
| Minotaur IV HAPS | United States |
Orbital Sciences | 23.88 | 2.34 | 86.3 | 2010 | - | 1/1 | Active | |||
| 3-stage PSLV | 2S+1L | India |
ISRO | 2.8 | 500 | - | - | 0/0 | Development | |||
| Vega | 3S+1L |  European Union |
ESA / ISA | 30 | 3 | 137 | 2000(?) | SSO: 1500 | 2012 | - | 6/6 | Active |
See also
- Comparison of orbital rocket engines
- Comparison of orbital launch systems
- Comparison of orbital launchers families
- Comparison of orbital spacecraft
- Comparison of space station cargo vehicles
- List of space launch system designs
- List of orbital launch systems
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