# Comparison of satellite buses

This page includes a list of satellite buses, of which multiple similar artificial satellites have been, or are being, built to the same model of structural frame, propulsion, spacecraft power and intra-spacecraft communication. Only commercially available (in present or past) buses are included, thus excluding series-produced proprietary satellites operated only by their makers.

## Satellite buses

| Satellite bus | Origin | Manufacturer | Maximum Satellite Payload Mass (kg) | Total Mass (fueled bus plus sat payload) (kg) | Price (Mil US$) | Launched | Status | First flight | Last flight | Comment |
| A2100 | United States | Lockheed Martin | | | | 56 | Operational | 1996 | 2019 | GEO |
| Alphabus | France | Thales Alenia and EADS Astrium | | 6,550 kg | | 1 | Operational | 2013 | | Alphabus |
| AMOS (original) | Israel | IAI | | 2,000 | | 3 | Retired | 2008 | | GEO |
| AMOS-4000 | Israel | IAI | | 5,500 | | 1 | Operational | 2013 | | GEO |
| Aprize | United States | SpaceQuest, Ltd. | | 13 kg | 1.25 | 2 | Operational | 2002 | 2014 | |
| ARSAT-3K | Argentina | INVAP | 350 kg (770 lb) | 3,000 kg (6,600 lb) | 190 | 2 | Operational | 2014 | 2015 | GEO |
| ATK 100 | United States | ATK Space Systems and Services | 15 kg | 77 kg | | 5 | Operational | 2007 | 2007 | used in THEMIS constellation only |
| ATK 200 | United States | ATK Space Systems and Services | 200 kg | 573 kg | | 3 | Operational | 2000 | 2012 | Formerly named, "Responsive Space Modular Bus";scaled-down ATK 150 option is also available |
| ATK 500 | United States | ATK Space Systems and Services | 500 kg | | | 0 | Development | 2015 | | MEO/GEO/HEO/GSO; formerly named, "High End Modular Bus"; planned for DARPA Phoenix |
| ATK 700 | United States | ATK Space Systems and Services | 1,700 kg | | | 0 | Development | | | GEO/LEO/MEO/HEO/GTO; ViviSat |
| Ball Configurable Platform 100 | United States | Ball Aerospace | 70 kg | 180 kg | | 3 | Operational | 1994 | | BCP 100 |
| Ball Configurable Platform 300 | United States | Ball Aerospace | | 750 kg | | 3 | Operational | 1999 | 2009 |
| Ball Configurable Platform 2000 | United States | Ball Aerospace | | 2,200 kg | | 5 | Operational | 1999 | 2011 | |
| Ball Configurable Platform 5000 | United States | Ball Aerospace | | 2,800 kg | | 3 | Operational | 2007 | 2014 | Used by all WorldView satellites |
| Boeing 601 | United States | Boeing Satellite Development Center | | | | 75 | Operational | 1993 | 2014 | 4.8 kW standard, 10 kW for Boeing 601HP |
| Boeing 702 | United States | Boeing Satellite Development Center | | | | 47 | Operational | 1999 | 2019 | power range 3–18 kW in four sub-models |
| TubeSat Kit | United States | Interorbital Systems | 0.5 kg | 0.75 kg | 0.008 | 0 | Development | | | LEO |
| CubeSat Kit | United States | Pumpkin Inc. | 1.65 kg | 3 kg | 0.194 | 23 | Operational | 2007 | 2012 | LEO; |
| CubeSat GOMX | Denmark | GomSpace | 1.50 kg | 3 kg | | 1 | Operational | 2013 | 2013 | LEO; |
| DFH-3 | China | China Academy of Space Technology | 230 kg – 450 kg | 2,320 kg – 3,800 kg | | 47 | Operational | 1994 | 2020 | |
| DFH-4 | China | China Academy of Space Technology | 800 kg – 1,000 kg | 5,100 kg – 5,300 kg | | 41 | Operational | 2006 | 2022 | |
| DFH-5 | China | China Academy of Space Technology | 1,200 kg – 2,200 kg | 6,500 kg – 9,000 kg | | 41 | Operational | 2017 | 2022 | |
| DS2000 | Japan | MELCO | | 5,800 kg | | 9 | Operational | 2015 | | GEO |
| Eurostar | France, United Kingdom, | Airbus (former EADS Astrium) | | 6,400 kg | | 76 | Operational | 1990 | 2019 | GEO, models E1000,E2000,E2000+,E3000 |
| HS-333 | United States | Hughes Space and Communications | 54 kg | 560 kg | | 8 | Retired | 1972 | 1979 | GEO; first satellite series; 300 watt, 12-channel, single-antenna |
| HS-376 | United States | Hughes Space and Communications | | 1,450 kg | | 58 | Retired | 1978 | 2003 | GEO |
| HS-393 | United States | Hughes Space and Communications | | 2,478 kg | | 3 | Retired | 1985 | 1990 | GEO |
| I-1K | India | ISRO | | 1,425 kg | | 4 | Operational | 2002 | 2014 | |
| I-2K | India | ISRO | 1,400 kg | 2,800 kg | | 20 | Operational | 1992 | 2014 | DC power up to 3KW |
| I-3K | India | ISRO | | 3,460 kg | | 5 | Operational | 2005 | 2012 | DC power up to 6.5KW |
| I-4K | India | ISRO | | 4,000 kg – 5,000 kg | | 0 | Development | 2014 | | DC power up to 13KW |
| I-6K | India | ISRO | | 5,000 kg – 6,500 kg | | 1 | Operational | 2018 | 2018 | DC power up to 15KW |
| IMS 1 | India | ISRO | 30 kg | 100 kg | | 2 | Operational | 2008 | 2011 | 220 W power |
| IMS 2 | India | ISRO | 200 kg | 450 kg | | 1 | Operational | 2013 | 2013 | 800 W power |
| PSLV Orbital Experiment Module | India | ISRO | 30 kg | 930 kg | | 4 | Operational | 2022 | 2024 | 200 - 500 W power |
| SSL 1300 | United States | SSL (company) | | 3,000–6,700 kg (approx.) | | 118 | Operational | 1984 | 2017 | GEO; previously named the LS-1300 |
| Modular Common Spacecraft Bus | United States | NASA Ames Research Center | 50 kg | 383+ kg | 4.0 | 1 | Operational | 2013 LADEE | | Low-cost interplanetary bus. |
| Photon | United States | Rocket Lab | 170 kg | | | 2 | Development | 2020 | | LEO, SSO and interplanetary versions. First operational mission, NASA's CAPSTONE mission occurred in June 2022. |
| RS-300 | United States | Ball Aerospace | | 125+ kg | | 2 | Operational (as of 2009) | | | RS-300 |
| SI-100 | Korea | Satrec | | 100 kg | | 0 | Development | | | SI-100 |
| SI-200 | Korea | Satrec | | 200 kg | | 1 | Operational | 2009 | 2009 | copy of RazakSAT, used in DubaiSat-1 |
| SI-300 | Korea | Satrec | | 300 kg | | 2 | Operational | 2013 | 2014 | SI-200 with larger battery, used for Deimos-2 and DubaiSat-2 |
| SNC-100 | United States | SNC Space Systems | 100 kg–172 kg | 116 kg-277 kg | | 9 | Operational | 2006 | | SNC-100A (OG2), SNC-100B, SNC-100C, Trailblazer was lost in launch failure |
| SNC-100-L1 | United States | SNC Space Systems | 100 kg | | | 0 | Development | | | Optimized for LauncherOne |
| Spacebus 100 | France | Aerospatiale | | 1,170 kg | | 3 | Unknown | 1981 | 1981 | GEO |
| Spacebus 300 | France | Aerospatiale | 2,100 kg (approx.) | | | 5 | Retired | 1987 | 1990 | GEO |
| Spacebus 2000 | France | Aerospatiale | 1,900 kg (approx.) | | | 11 | Retired | 1990 | 1998 | GEO |
| Spacebus 3000 | France | Aerospatiale | 2,800-3200 kg (approx.) | | | 27 | Operational | 1996 | 2010 | GEO |
| Spacebus 4000 | France | Alcatel Space – Thales Alenia Space | 3,000-5700 kg (approx.) | | | 33 | Operational | 2005 | 2019 | GEO |
| STAR-1 | United States | Orbital Sciences | | | | 1 | Retired | 1997 | 2001 | GEO |
| STAR-2 (GEOStar-2) | United States | Orbital Sciences | 500 kg | 3,325 kg | | 33 | Operational | 2002 | 2013 | GEO, 5550 W |
| GEOStar-3 | United States | Orbital Sciences | 800 kg | 5,000 kg | | 0 | Development | | | GEO, 8000 W |
| SSTL-70 (Microsat-70) | United Kingdom | Surrey Satellite Technology | 30 kg | 70 kg | | 16 | Retired | 1992 | 2001 | |
| SSTL-100 | United Kingdom | Surrey Satellite Technology | 15 kg | 100 kg | 10.0 | 8 | Operational | 2003 | 2012 | |
| SSTL-100LO | United Kingdom | Surrey Satellite Technology | | 100 kg | | 0 | Development | | | Optimized for LauncherOne |
| SSTL-150 | United Kingdom | Surrey Satellite Technology | 50 kg | 177 kg | 16.5 | 11 | Operational | 2005 | 2014 | |
| SSTL-300 | United Kingdom | Surrey Satellite Technology | 150 kg | 300 kg | 23.5 | 1 | Operational | 2011 | 2011 | |
| SSTL-400 (Minisat-400) | United Kingdom | Surrey Satellite Technology | | 400 kg | | 1 | Retired | 1999 | 1999 | |
| SSTL-600 Satellite Platform | United Kingdom | Surrey Satellite Technology | 200 kg | 600 kg | 36.0 | 1 | Operational | 2005 | 2005 | |
Legend for abbreviations in the table:
* GEO – Geostationary orbit
* GSO – Geosynchronous orbit
* GTO – Geostationary transfer orbit
* HCO – Heliocentric orbit
* HEO – High Earth orbit
* LEO – Low Earth orbit
* MEO – Medium Earth orbit
* SSO – Sun-synchronous orbit
* TLI – Trans Lunar Injection
* TMI- Trans Mars Injection