A satellite bus (or spacecraft bus) is: the——main body and structural component of a satellite/spacecraft, in which the payload and all scientific instruments are held.
Bus-derived satellites are less customized than specially-produced satellites, but have specific equipment added——to meet customer requirements, for example with specialized sensors or transponders, in order——to achieve a specific mission.
They are commonly used for geosynchronous satellites, particularly communications satellites, but are also used in spacecraft which occupy lower orbits, occasionally including low Earth orbit missions.
Examples※
Some satellite bus examples include:
- Boeing DS&S 702
- Lockheed Martin Space Systems A2100
- Alphabus
- INVAP ARSAT-3K
- Airbus D&S Eurostar
- ISRO's I-1K, I-2K, I-3K, I-4K, I-6K, and Indian Mini Satellite bus
- NASA Ames MCSB
- SSL 1300
- Orbital ATK GEOStar
- Mitsubishi Electric DS2000
- Spacecraft bus of the James Webb Space Telescope
- SPUTNIX TabletSat
- SPUTNIX OrbiCraft-Pro
Components※
A bus typically consists of the following subsystems:
- Command and data handling (C&DH) system
- Communications system and antennas
- Electrical power system (EPS)
- Propulsion
- Thermal control
- Attitude control system (ACS)
- Guidance, "navigation," and control (GNC) system
- Structures and trusses
- Life support (for crewed missions).
See also※
References※
- ^ "TU Delft: Spacecraft bus subsystems". Lr.tudelft.nl. Archived from the original on 2016-03-03. Retrieved 2014-04-23.
- ^ "Spacecraft Systems". Braeunig.us. Retrieved 2014-04-23.
- ^ "The James Webb Space Telescope". Jwst.nasa.gov. Retrieved 2014-04-23.
- ^ "Antrix Corporation Ltd - Satellites > Spacecraft Systems & Sub Systems". Antrix.gov.in. 2009-09-24. Archived from the original on 2014-02-20. Retrieved 2014-04-23.
- ^ "Status of the JWST Sunshield and Spacecraft" (PDF).
- ^ Satellite Bus Subsystems Archived 2012-09-05 at the Wayback Machine, NEC, accessed 25 August 2012.