Indian Mini Satellite (IMS) is a family of modular^{[1]} mini satellite buses developed by the Indian Space Research Organisation (ISRO).^{[2]}^{[3]}
Feature  IMS1^{[4]}^{[5]}^{[predatory publisher]}  IMS2^{[5]}^{[6]}  IMS3 (Planned IMS2 Derivative)^{[7]} 
Launch Mass  100 kilograms (220 lb)  450 kilograms (990 lb)  450 kilograms (990 lb) 
Maximum bus mass  70 kilograms (150 lb)  250 kilograms (550 lb)  250 kilograms (550 lb) 
Payload mass  30 kilograms (66 lb)  200 kilograms (440 lb)  200 kilograms (440 lb) 
Propellant  3.5 kilograms (7.7 lb)  21 kilograms (46 lb)  
Design lifetime  2 years  5 years  
Raw bus voltage  2833 Volts  2833 Volts  2842 Volts 
Solar Array Power  230 Watts (EOL)  675 Watts (EOL) 850 Watts (BOL) 
850 Watts (BOL) 
Payload power  30 Watts (Continuous) 70 Watts (Duty Cycle) 
250 Watts (Continuous) 600 Watts (Duty Cycle) 
250 Watts (Continuous) 400 Watts (Duty Cycle) 
Attitude Control  3axis stabilized Four Reaction Wheels Single 1N thruster 
3axis stabilized Four Reaction Wheels Monopropellant RCS Four 1N thrusters Four 0.2N thrusters 

Pointing Accuracy  ± 0.1° (all axis)  ± 0.1° (all axis)  
SSR Storage  16 Gb  32 Gb (SDRAM) 256 Gb (Flash Memory) 
32 Gb (SDRAM) 256 Gb (Flash Memory) 
Payload data storage  ≤ 16 Gb  ≤ 32 Gb  
Downlink  ≤ 8 Mbit/s DL rate  ≤ 105 Mbit/s DL rate  ≤ 160 Mbit/s DL rate 
Missions  IMS1 ^{[8]} Youthsat ^{[9]} MicrosatTD^{[10]} 
SARAL ^{[11]} ScatSat1^{[12]} EMISAT^{[13]} HySIS XPoSat (Planned) 
