AstroSat - Spacecraft

The objectives of the AstroSat mission are to design, develop, realize and launch a multi-wavelength astronomy satellite for studying the cosmic sources simultaneously over a wide range of the electromagnetic spectrum i.e from optical, ultraviolet (UV) to high energy X-rays.  

Spacecraft mass ~ 1515 kg (Main bus: 660.2 kg; Payloads: 854.8 kg)
Spacecraft Cuboid shaped; 1.96 m x 1.75 m x 1.30 m
S/C power 1626 W
Structures 1500 kg class. Composite Fiber Reinforced Plastic (CFRP) honeycomb sandwich with CFRP face skin and aluminium honeycomb core.
Mechanism Solar Array Drive Mechanism (SADM), UVIT and SXT deployable cover, SSM hold down release and steering mechanism
Propulsion Monopropellant Hydrazine (42 kg) and 11 N thrusters (8 no.s)
Thermal System Passive thermal control system, Heaters and Radiator plates
Power System 2 wing assemblies, each having two panels (1.4m x 1.8 m each)of Advanced Triple Junction solar cells, ~ 2000 Watt generation, Two 36 AH Li ion batteries, SADA for sun tracking
Pointing accuracy 0.05 deg (3 sigma) in each axis
AOCS Drift Rate (freq < 0.2 Hz) : 3 x 10-4 deg/s Jitter (freq > 0.2 Hz) : < 0.3 arcsec
Sensors 4 Solar panel Sun sensor ; 2 nos. Star sensors (Mk-I) ; four 4 Pi Sun sensors, two triaxial magnetometer, Inertial Reference Unit
Actuators 10 NMs Reaction Wheels (4 Nos), 11 N Thrusters (8Nos)
Antenna Phased Array Antenna (PAA); TC (Uplink) – 2067.897 MHz; TM (Downlink) – 2245 MHz


AstroSat in Clean room before its integration with PSLV-C30

AstroSat in Clean room before its integration with PSLV-C30


Launch Mass: 1515 kg

Launch Date: September 28, 2015

Power: 1626 W

Launch Vehicle: PSLV-C30

Type of Satellite: Space Science & Exploration

Manufacturer: ISRO

Owner: ISRO

Orbit: 650 km, 6 deg inclination

Orbit Type: Near equatorial