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 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 [1] | Operational | 1996 | 2019 | GEO | |||
Alphabus | France | Thales Alenia [2] and EADS Astrium | 6,550 kg[ citation needed ] | 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 [3] | 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 [4] | 77 kg | 5 [5] | Operational | 2007 | 2007 | used in THEMIS constellation only | |
ATK 200 | United States | ATK Space Systems and Services | 200 kg [4] | 573 kg | 3 [5] | 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 [4] | 0 | Development | 2015 | MEO/GEO/HEO/GSO; formerly named, "High End Modular Bus"; planned for DARPA Phoenix [4] | |||
ATK 700 | United States | ATK Space Systems and Services | 1,700 kg [4] | 0 | Development | GEO/LEO/MEO/HEO/GTO; ViviSat [6] | ||||
Ball Configurable Platform 100 | United States | Ball Aerospace | 70 kg | 180 kg | 3 [7] | Operational | 1994 [7] | BCP 100 [8] | ||
Ball Configurable Platform 300 | United States | Ball Aerospace | 750 kg | 3 [9] | Operational | 1999 | 2009 | |||
Ball Configurable Platform 2000 | United States | Ball Aerospace | 2,200 kg | 5 [9] | 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 [10] | Operational | 1999 | 2019 | power range 3–18 kW in four sub-models | |||
TubeSat Kit [11] | United States | Interorbital Systems | 0.5 kg | 0.75 kg | 0.008 [12] | 0 | Development | LEO | ||
CubeSat Kit [4] | United States | Pumpkin Inc. | 1.65 kg | 3 kg | 0.194 [13] | 23 | Operational | 2007 | 2012 | LEO; |
CubeSat GOMX [14] | 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 [15] | 560 kg [16] | 8 [16] | Retired | 1972 | 1979 [16] | GEO; first satellite series; 300 watt, 12-channel, single-antenna | |
HS-376 | United States | Hughes Space and Communications | 1,450 kg [17] | 58 [17] | Retired | 1978 | 2003 [17] | GEO | ||
HS-393 | United States | Hughes Space and Communications | 2,478 kg [18] | 3 [18] | Retired | 1985 | 1990 [18] | GEO | ||
I-1K | India | ISRO | 1,425 kg [19] | 4 | Operational | 2002 | 2014 | |||
I-2K | India | ISRO | 1,400 kg | 2,800 kg [20] | 20 | Operational | 1992 | 2014 | DC power up to 3KW | |
I-3K | India | ISRO | 3,460 kg [21] | 5 | Operational | 2005 | 2012 | DC power up to 6.5KW | ||
I-4K | India | ISRO | 4,000 kg – 5,000 kg [22] [23] | 0 | Development | 2014 | DC power up to 13KW | |||
I-6K | India | ISRO | 5,000 kg – 6,500 kg [24] [25] | 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 [26] [27] [28] | 1 | Operational | 2013 | 2013 | 800 W power | |
PSLV Orbital Experiment Module | India | ISRO | 30 kg | 930 kg | 4 | Operational | 2022 | 2024 [29] | 200 - 500 W power | |
SSL 1300 | United States | SSL (company) | 3,000–6,700 kg (approx.) [30] | 118 | Operational | 1984 [30] | 2017 | GEO; previously named the LS-1300 | ||
Modular Common Spacecraft Bus | United States | NASA Ames Research Center | 50 kg | 383+ kg [31] | 4.0 | 1 | Operational | 2013 LADEE | Low-cost interplanetary bus. [32] | |
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 [33] | 2 | Operational (as of 2009 [update] ) | RS-300 | ||||
SI-100 | Korea | Satrec | 100 kg [34] | 0 | Development | SI-100 | ||||
SI-200 | Korea | Satrec | 200 kg [35] | 1 | Operational | 2009 | 2009 | copy of RazakSAT, used in DubaiSat-1 | ||
SI-300 | Korea | Satrec | 300 kg [36] | 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 [37] –172 kg [38] | 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 [39] | 0 | Development | Optimized for LauncherOne [39] | ||||
Spacebus 100 | France | Aerospatiale | 1,170 kg [40] | 3 | Unknown [41] | 1981 [40] | 1981 | GEO | ||
Spacebus 300 | France | Aerospatiale | 2,100 kg (approx.)[ citation needed ] | 5 | Retired | 1987 | 1990 | GEO | ||
Spacebus 2000 | France | Aerospatiale | 1,900 kg (approx.)[ citation needed ] | 11 | Retired | 1990 | 1998 | GEO | ||
Spacebus 3000 | France | Aerospatiale | 2,800-3200 kg (approx.)[ citation needed ] | 27 | Operational[ citation needed ] | 1996 | 2010 | GEO | ||
Spacebus 4000 | France | Alcatel Space – Thales Alenia Space | 3,000-5700 kg (approx.)[ citation needed ] | 33 | Operational[ citation needed ] | 2005 | 2019 | GEO | ||
STAR-1 | United States | Orbital Sciences | 1 | Retired | 1997 [42] | 2001 | GEO | |||
STAR-2 (GEOStar-2) | United States | Orbital Sciences | 500 kg | 3,325 kg | 33 [43] | Operational | 2002 [42] | 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 [39] | 0 | Development | Optimized for LauncherOne [39] | ||||
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:
Boeing 702 is a communication satellite bus family designed and manufactured by the Boeing Satellite Development Center, and flown from the late-1990s into the 2020s. It covers satellites massing from 1,500 kg (3,300 lb) to 6,100 kg (13,400 lb) with power outputs from 3 to 18 kW and can carry up to approximately 100 high-power transponders.
JSAT Corporation (JSAT) was the first private Japanese satellite operator, which owned the JSAT satellites, as well as operated and partially owned the N-Star with NTT DoCoMo. Its origins can be traced to the funding of Japan Communications Satellite Company (JCSAT) and Satellite Japan Corporation in 1985. Both companies merged into Japan Satellite Systems Inc. in 1993. In 2000 the company was renamed as JSAT Corporation and was listed in the First Section of the Tokyo Stock Exchange. On September 1, 2008, the company was merged into the SKY Perfect JSAT Group.
This comparison of orbital launch systems lists the attributes of all current and future individual rocket configurations designed to reach orbit. A first list contains rockets that are operational or have attempted an orbital flight attempt as of 2024; a second list includes all upcoming rockets. For the simple list of all conventional launcher families, see: Comparison of orbital launchers families. For the list of predominantly solid-fueled orbital launch systems, see: Comparison of solid-fueled orbital launch systems.
A satellite bus is the main body and structural component of a satellite or spacecraft, in which the payload and all scientific instruments are held.
The Broadcasting Satellite System Corporation (B-SAT) is a Japanese corporation established in April 1993 to procure, manage and lease transponders on communications satellites. Its largest stockholder, owning 49.9%, is NHK, the Japan Broadcasting Corporation. In 1994, it was ranked by Space News as the world's 19th largest fixed satellite operator.
In 1970, Hughes Aircraft Company (HAC) Space and Communications Group offered the first standardized satellite: the HS 333 design. A spinning satellite, it was based on previous one-design satellites like Intelsat I. HAC built eight of these 300 watt, 12 channel single antenna satellites between 1970 and 1977.
GOES-4, known as GOES-D before becoming operational, was a geostationary weather satellite which was operated by the United States National Oceanic and Atmospheric Administration as part of the Geostationary Operational Environmental Satellite system. Launched in 1980, it was used for weather forecasting in the United States, and later in Europe. Following its retirement it became the first satellite to be sent into a graveyard orbit.
INSAT-3C is a multipurpose satellite built by ISRO and launched by Arianespace in Jan 2002. INSAT-3C is the second satellite of the INSAT-3 series. All the transponders provide coverage over India. Insat-3C is controlled from the Master Control Facility at Hassan in Karnataka. It will provide voice, video and digital data services to India and neighboring countries.
This article compares different orbital launcher families. The article is organized into two tables: the first contains a list of currently active and under-development launcher families, while the second contains a list of retired launcher families.
I-1K is a satellite bus developed by the Indian Space Research Organisation (ISRO) and marketed by Antrix Corporation. The I-1K bus is designed to be compatible with lightweight geostationary satellites and is commonly used for meteorological satellites.
I-3K or the INSAT 3000 is a satellite bus developed by Indian Space Research Organisation (ISRO), and marketed by Antrix Corporation and New Space India Ltd. It is the standard bus for 3,000-kg class satellites; the 'I' in I-3K stands for INSAT, a group of communication satellites developed and launched by ISRO. The I-3K bus can supply DC power up to 6500 watts, and is suitable for satellites with lift-off mass in range of 3,000-3,400 kg.
BSAT-1a was a geostationary communications satellite designed and manufactured by Hughes on the HS-376 platform. It was originally ordered and operated by the Broadcasting Satellite System Corporation (B-SAT). It was used as the main satellite to broadcast television channels for NHK and WOWOW over Japan. It had a pure Ku band payload and operated on the 110°E longitude until it was replaced, along its backup BSAT-1b, by BSAT-3a. On 3 August 2010, it was decommissioned and placed on a graveyard orbit.
BSAT-1b was a geostationary communications satellite designed and manufactured by Hughes on the HS-376 platform. It was originally ordered and operated by the Broadcasting Satellite System Corporation (B-SAT). It was used as backup of BSAT-1a to broadcast television channels for NHK and WOWOW over Japan. It had a pure Ku band payload and operated on the 110°E longitude until it was replaced, along its twin BSAT-1a, by BSAT-3a.
The JSAT constellation is a communication and broadcasting satellite constellation formerly operated by JSAT Corporation and currently by SKY Perfect JSAT Group. It has become the most important commercial constellation in Japan, and fifth in the world. It has practically amalgamated all private satellite operators in Japan, with only B-SAT left as a local competitor.
The Boeing 376 is a communications satellite bus introduced in 1978 by Hughes Space and Communications Company. It was a spin-stabilized bus, a successor to Hughes HS-333.
SBS 2 was a geostationary communications satellite designed and manufactured by Hughes on the HS-376 platform. It was ordered by Satellite Business Systems, which later sold it to Hughes Communications. It had a Ku band payload and operated on the 117°W longitude.
SBS 6 was a geostationary communications satellite designed and manufactured by Hughes on the HS-393 platform. It was originally ordered by Satellite Business Systems, which later sold it to Hughes Communications and was last used by Intelsat. It had a Ku band payload and operated on the 95°W longitude.
The Hughes 393 is a communications satellite bus introduced in 1985 by Hughes Space and Communications Company. It was a spin-stabilized bus that had twice as much power as the HS-376 platform.
The BT-4 is a pressure-fed liquid rocket engine designed and manufactured by IHI Aerospace of Japan. It was originally developed for the LUNAR-A project, but it has been used as a liquid apogee engine in some geostationary communications satellite based on the Lockheed Martin A2100 and GEOStar-2 satellite buses. It has also been used on the HTV and Cygnus automated cargo spacecraft.
The GEOStar is a family of satellite buses designed and manufactured by Northrop Grumman Innovation Systems. The family initially focused on small geostationary communications satellites. The first iterations addressed the sub-5 kW commercial segment that was underserved following the retirement of the HS-376 satellite bus. It started with the STARBus on CTA Space Systems, which was later bought successively by Orbital Sciences, Orbital ATK, and most recently Northrop Grumman Innovation Systems.
ATK A100 THEMIS; ATK A200 ORS-1, TacSat3, and EO-1; ATK A500 DARPA Phoenix; ATK A700 ViviSat
first 18 satellites [are] in production
develop versions of their smallsat bus optimized to the design of LauncherOne.
It is not clear from the sources if the Spacebus 100 satellite bus is still on offer.