NGIS's GEOStar-2 bus design is unique within the satellite industry. NGIS's GEOStar-2 bus provides an affordable low-to-medium power satellite platform that is ideal for missions of this size. Rather than being a less efficient version of a larger, heavier product, NGIS's GEOStar-2 bus is designed specifically for the 1000 to 5550 watts payload class.[1]
Designedit
The GEOStar-2 bus satellite is a modular, mass efficient structure, designed for simplified integration to reduce manufacturing cycle times. The structure is supported by a composite thrust cylinder, to which the bus, payload, nadir and base panels are connected. Energy from two multi-panel solar wings and lithium-ion batteries is electronically processed to provide 36 volts regulated power to the satellite throughout the mission. All active units aboard the satellite are connected through a 1553 data bus. Commands and telemetry are processed through the flight software resident on the flight processor, which provides robust autonomous control to all GEOStar-2 satellites. The modularity of the structure and the standard 1553 interfaces allow parallel assembly and test of the bus and payload systems, reducing manufacturing schedule risk by minimizing the time spent in serial satellite integration and test flow.[1] GEOStar-2 is designed for missions up to 15 years in duration. The propulsion system is sized for ten years of station keeping in geosynchronous orbit. Built-in radiation hardness for the severe geosynchronous environment is achieved through conservative selection of electronic parts.[2] Several available options augment the basic bus to provide improved pointing, more payload power, secure communications, higher downlink data rates or enhanced payload computing power.
While primary applications are Fixed-Satellite Services (FSS) and Broadcast Satellite Services (BSS), the GEOStar-2 bus can be adapted for MSS, Earth and space science applications, as well as for technology demonstration or risk reduction programs. Depending on mission duration requirements, the GEOStar-2 bus can accommodate payloads in excess of 500 kilograms, and provide up to 5550 watts of power. Instrument data can be provided in standard format such as CCSDS or through secured encryption, as approved by the National Security Agency (NSA).[1]
Shared launch opportunitiesedit
Due to the size and mass envelope of the satellite, the GEOStar-2 bus is compatible with almost all commercially available launch vehicles, maximizing opportunity for launch and access to space. While dedicated or single launch services are more readily available, the GEOStar-2 bus targets shared launch opportunities, where launch cost and launch-sharing opportunities are favorable.[1]
Mission servicesedit
Customers can purchase the GEOStar-2 bus spacecraft bus alone, or as part of a turn-key service that includes an integrated payload, network operations center and launch vehicle. NGIS conducts spacecraft commissioning from its own ground station prior to transferring spacecraft control to the customer's operations center.[1]
^"→ Star-2 → GeoStar-2". 20 February 2020. Retrieved 16 June 2020.
January 01, 1970
geostar, this, article, about, orbital, science, corp, satellite, platform, others, star, disambiguation, star, fully, redundant, flight, proven, spacecraft, designed, geosynchronous, missions, satellite, platform, designed, developed, thomas, heyden, indonesi. This article is about the Orbital Science Corp satellite platform For others see two star disambiguation The STAR 2 Bus is a fully redundant flight proven spacecraft bus designed for geosynchronous missions It is a satellite platform designed and developed by Thomas van der Heyden for the Indonesian Cakrawarta satellite program in the early 1990s now manufactured by Northrop Grumman Innovation Systems with an apogee kick motor to place a communications satellite into geostationary orbit a thruster to provide the satellite with orbital station keeping for a 15 year mission and solar arrays to provide the satellite payload with 5 kW of electrical power 1 Contents 1 Advantages 2 Design 2 1 Structure 2 2 Power subsystem 2 3 Attitude control subsystem 2 4 Command and data handling subsystem 3 Payload support 3 1 Shared launch opportunities 3 2 Mission services 4 Satellite Orders 5 See also 6 ReferencesAdvantages editNGIS s GEOStar 2 bus design is unique within the satellite industry NGIS s GEOStar 2 bus provides an affordable low to medium power satellite platform that is ideal for missions of this size Rather than being a less efficient version of a larger heavier product NGIS s GEOStar 2 bus is designed specifically for the 1000 to 5550 watts payload class 1 Design editThe GEOStar 2 bus satellite is a modular mass efficient structure designed for simplified integration to reduce manufacturing cycle times The structure is supported by a composite thrust cylinder to which the bus payload nadir and base panels are connected Energy from two multi panel solar wings and lithium ion batteries is electronically processed to provide 36 volts regulated power to the satellite throughout the mission All active units aboard the satellite are connected through a 1553 data bus Commands and telemetry are processed through the flight software resident on the flight processor which provides robust autonomous control to all GEOStar 2 satellites The modularity of the structure and the standard 1553 interfaces allow parallel assembly and test of the bus and payload systems reducing manufacturing schedule risk by minimizing the time spent in serial satellite integration and test flow 1 GEOStar 2 is designed for missions up to 15 years in duration The propulsion system is sized for ten years of station keeping in geosynchronous orbit Built in radiation hardness for the severe geosynchronous environment is achieved through conservative selection of electronic parts 2 Several available options augment the basic bus to provide improved pointing more payload power secure communications higher downlink data rates or enhanced payload computing power Structure edit Bus Dimensions H x W x L 1 75 x 1 7 x 1 8 m Construction Composite Al 1 Power subsystem edit Payload Power Up to 5550 watts orbit average at 15 years Bus Voltage 24 36 VDC nominal Solar Arrays multi junction GaAs cells Batteries lithium ion 1 Attitude control subsystem edit Stability Mode 3 axis zero momentum Propulsion Subsystem Transfer Orbit System liquid bi propellant On Orbit monopropellant hydrazine 1 Command and data handling subsystem edit Flight Processor MIL STD 1750A Interface Architecture MIL STD 1553B CCSDS 1 Payload support editWhile primary applications are Fixed Satellite Services FSS and Broadcast Satellite Services BSS the GEOStar 2 bus can be adapted for MSS Earth and space science applications as well as for technology demonstration or risk reduction programs Depending on mission duration requirements the GEOStar 2 bus can accommodate payloads in excess of 500 kilograms and provide up to 5550 watts of power Instrument data can be provided in standard format such as CCSDS or through secured encryption as approved by the National Security Agency NSA 1 Shared launch opportunities edit Due to the size and mass envelope of the satellite the GEOStar 2 bus is compatible with almost all commercially available launch vehicles maximizing opportunity for launch and access to space While dedicated or single launch services are more readily available the GEOStar 2 bus targets shared launch opportunities where launch cost and launch sharing opportunities are favorable 1 Mission services edit Customers can purchase the GEOStar 2 bus spacecraft bus alone or as part of a turn key service that includes an integrated payload network operations center and launch vehicle NGIS conducts spacecraft commissioning from its own ground station prior to transferring spacecraft control to the customer s operations center 1 Satellite Orders editSatellite Country Operator Type Transponders Launch date UTC Rocket Changes Status AMC 21 United States SES Americom Television broadcasting 24 Ku band 14 August 2008 Ariane 5 ECA Active Amazonas 4A Spain Hispasat Communications 24 Ku band 14 August 2008 Ariane 5 ECA Active Azerspace 1 Africasat 1a Azerbaijan Azercosmos Communications 24 C band 12 Ku band 7 February 2013 Ariane 5 ECA Active Eutelsat 5 West B International Eutelsat Communications 35 Ku band 9 October 2019 Proton MPhase 4 Active Galaxy 12 United States PanAmSat Television broadcasting 20 24 C band 9 April 2003 Ariane 5 G Active Galaxy 14 United States PanAmSat Television broadcasting 20 24 C band 13 August 2005 Soyuz FG Active Galaxy 15 United States PanAmSat Television broadcasting 20 24 C band 13 October 2005 Ariane 5 GS Active Galaxy 30 United States Intelsat Television broadcasting C band Ku band Ka band and WAAS payload 15 August 2020 Ariane 5 ECA Active Horizons 2 United States Japan PanAmSat SKY Perfect JSAT Communications 20 Ku band 21 December 2007 Ariane 5 GS Active HYLAS 2 United Kingdom Avanti Communications Satellite internet 24 Ka band 2 August 2012 Ariane 5 ECA Active Intelsat 11 United States Intelsat Communications 16 C band 18 Ka band 5 October 2007 Ariane 5 GS Formerly PAS 11 Active Intelsat 15 United States Intelsat Communications 22 Ku band 30 November 2009 Zenit 3SLB Active Intelsat 16 United States Intelsat Communications 24 Ku band 12 February 2010 Proton MPhase 1 Formerly PAS 11R Active Intelsat 18 United States Intelsat Communications 24 C band 12 Ku band 5 October 2011 Zenit 3SLB Active Intelsat 23 United States Intelsat Communications 24 C band 15 Ku band 14 October 2012 Proton MPhase 3 Active Koreasat 6 South Korea KT Corporation Television broadcasting 30 Ku band 29 December 2010 Ariane 5 ECA Active MEASAT 3a Malaysia MEASAT Satellite Systems Television broadcasting 12 C band 12 Ku band 21 June 2009 Zenit 3SLB Active Mexsat 3 Mexico Mexican Satellite System Mobile communications 12 C band 12 Ku band 19 December 2012 Ariane 5 ECA Active N STAR c Japan NTT Docomo Mobile communications 1 C band 20 S band 5 July 2002 Ariane 5 G Retired New Dawn United States Intelsat Television broadcasting 28 C band 24 Ku band 22 April 2011 Ariane 5 ECA Known as Intelsat 28 Active NSS 9 Netherlands SES World Skies Communications 28 C band 12 February 2009 Ariane 5 ECA Active Optus D1 Australia Optus Television broadcasting 24 Ku band 13 October 2006 Ariane 5 ECA Active Optus D2 Australia Optus Television broadcasting 24 Ku band 5 October 2007 Ariane 5 GS Active Optus D3 Australia Optus Television broadcasting 24 Ku band 21 August 2009 Ariane 5 ECA Active SES 1 United States SES Americom Communications 24 C band 24 Ku band 2 Ka band 24 April 2010 Proton MPhase 2 Formerly AMC 4R Active SES 2 and CHIRP Commercially Hosted InfraRed Payload United States SES Americom Communications 24 C band 24 Ku band 2 Ka band 21 September 2011 Ariane 5 ECA Formerly AMC 5R Active SES 3 United States SES Americom Communications 24 C band 24 Ku band 2 Ka band 15 July 2011 Proton MPhase 3 Active SES 8 Luxembourg SES Television broadcasting 33 Ku band 3 December 2013 Falcon 9 Active Sky Mexico 1 Mexico DirecTV Television broadcasting 24 Ku band 2 R band 27 May 2015 Ariane 5 ECA Known as SKYM 1 Active Star One C3 Brazil Star One Communications 28 C band 16 Ku band 10 November 2012 Ariane 5 ECA Active Telkom 2 Indonesia Telkom Indonesia Communications 24 C band 16 November 2005 Ariane 5 ECA Retired Thaicom 6 Thailand Thaicom Communications 24 C band 9 Ku band 6 January 2014 Falcon 9 Known as AfriCom 1 Active Thaicom 8 Thailand Thaicom Communications 24 Ku band 27 May 2016 Falcon 9 Active Thor 5 Norway Telenor Television broadcasting 24 Ku band 11 February 2008 Proton MPhase 3 ActiveSee also edit nbsp Spaceflight portal Star Bus GEOStar Northrop Grumman Innovation SystemsReferences edit a b c d e f g h i j Orbital ATK PDF Orbital com Retrieved 2015 10 12 Star 2 GeoStar 2 20 February 2020 Retrieved 16 June 2020 Retrieved from https en wikipedia org w index php title GEOStar 2 amp oldid 1221115623, wikipedia, wiki, book, books, library,
