A satellite bus (or spacecraft bus) is the main body and structural component of a satellite or 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 or transponders, in order to achieve a specific mission.
They are commonly used for geosynchronous satellites, particularly communications satellites, but are most commonly used in spacecraft which occupy low Earth orbit missions.
Examples
Some satellite bus examples include:
-
Boeing DS&S 702
-
Lockheed Martin Space Systems A2100
-
Moog Inc. SL-OMV, Meteor, Meteorite
-
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
-
family
-
Orbital ATK Star Bus family, inc GEOStar
-
Mitsubishi Electric DS2000
-
Spacecraft bus of the James Webb Space Telescope
-
SPUTNIX TabletSat-Aurora
-
SPUTNIX OrbiCraft-Pro
Components
A bus typically consists of the following subsystems:
[ Satellite Bus Subsystems , NEC, accessed 25 August 2012.]
-
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
External links
