Originally developed by CTA Space Systems, won its first order with IndoStar-1.[3]Orbital Sciences Corporation acquired CTA in 1997 and continued selling the platform under the STAR-1 designation.[4] It was able to sell three STAR-1 satellites to B-SAT of Japan, BSAT-2a, BSAT-2b and BSAT-2c. Orbital then introduced a new version of the platform known as STAR-2. Its first launch was with the sale of the satellite bus only, with N-STAR c.[1]
With the introduction of the LEOStar satellite bus, STAR-2 was renamed as GEOStar-2, a platform that eventually was capable of up to 5.5 kW of power production.[5][6] Orbital would later introduce the GEOStar-1 platform, capable of only 1.5 kW of power production. It is not to be confused with the original STAR-1, since GEOStar-1 is actually the project Aquila, a platform even smaller than the GEOStar-2 designed for military applications in geostationary orbit and medium Earth orbit.[7]
On March 10, 2014, Orbital introduced the GEOStar-3 platform. Not only was this a bigger platform that could generate up to 8 kW of power, but it also offered a satellite stacking feature for a dual launch option.[8][9] On April 29, 2014, Orbital Sciences announced that it would merge with Alliant Techsystems to create a new company called Orbital ATK, Inc. On February 9, 2015, Orbital ATK started operating as an entity.[10]
During 2015, Orbital ATK would introduce a variation of the bus dedicated to servicing spacecraft in geostationary orbit, the Gemini bus.[11] They would announce their first win for Gemini platform on April 12, 2016, with the agreement to sell the services of Mission Extension Vehicle-1toIntelsat in 2019.[12]
Through the years there have been different variations of the platform:
Gemini: platform designed for rendezvous capabilities. It can carry payloads with a mass of up to 1,700 kg (3,700 lb) and requiring up to 3 kW of power. Its expected design life is 6 to 15 years and has a 21 to 36 month to delivery lead time.[11]
GEOStar-1: micro platform for government satellite. It can carry payloads with a mass of up to 100 kg (220 lb) and requiring up to 1.5 kW of power. Its expected design life is 5 to 7 years and has a 27 to 30 month to delivery lead time.[7]
GEOStar-2 (originally STAR-2): small platform for commercial clients. It can carry payloads with a mass of up to 500 kg (1,100 lb) and requiring up to 5.5 kW of power. Its expected design life is 15 to 18 years and has a 24 to 27 month to delivery lead time.[6]
GEOStar-3: medium platform for commercial clients. It can carry payloads with a mass of up to 800 kg (1,800 lb) and requiring up to 8 kW of power. Its expected design life is 15 to 18 years and has a 27 to 30 month to delivery lead time.[9]
STAR-1 (originally STARBus): small commercial satellite platform. Originally developed by CTA, bought by Orbital Sciences Corporation. Could handle payloads with a mass of up to 200 kg (440 lb) and requiring up to 555 W of power. It used a solid Star 30CBPapogee kick motor for orbital circularization and had a 10-year design life.[13]
