The GOES-R spacecraft bus will be 3-axis stabilized and designed for 10 years of on-orbit operation preceded by up to 5 years of on-orbit storage. The satellite will be able to operate through periodic station-keeping and momentum adjust maneuvers, which will allow for near-continuous instrument observations. Other notable performance elements include: vibration isolation for the Earth-pointed optical bench and high-speed spacecraft-to-instrument interfaces designed to maximize science data collection. The cumulative time that GOES-R science data collection (including imaging) will be interrupted due to all momentum management, station-keeping, and yaw flip maneuvers will be under 120 minutes/year. This is a nearly two orders of magnitude improvement compared to the current GOES satellites. The spacecraft will carry three classifications of instruments: nadir-pointing, solar-pointing, and in-situ.
The satellite driving requirements are:
Spacecraft on-orbit life of 15 years with orbit East-West and North-South position maintained to within +/-0.1 degree
Collect and transmit up to 100Mbps Instrument Payload data from each location continuously
Continuous Rebroadcast function at L-Band up to 31 Mbps utilizing dual polarization
Provide continuing services [Search and Rescue, Data System Collection, Emergency Manager’s Weather Information Network (EMWIN)]
~5.5 meters (from launch vehicle interface to top of ABI)
Satellite (spacecraft and payloads) dry mass <2800kg
>4000W at end-of-life (includes accounting for limited array degradation)
The Spacecraft System Definition Review (SDR) was held in March 2010, the Preliminary Design Review (PDR) was completed in January 2011, and the Spacecraft successfully completed the Critical Design Review (CDR) in April 2012.
Lockheed Martin Space Systems Corporation began contract work on the spacecraft in July 2009. The scheduled start of integration and testing with the instruments is set for 2013. A derivative of the Lockheed Martin A2100 bus will be used for the GOES-R series.