Indian Space Research Organization, with a legacy over 30 years in satellite launching has an extensive range of Spacecraft separation systems catering up to 4000kg class payloads. The successful demonstration of highly reliable space mechanisms in different launch vehicles over the time has put ISRO among the leading launch service providers in the world today.
PRODUCTS IN A GLIMPSE
PAYLOAD SEPARATION MECHANISMS
INLS1U
- Non-Pyro dispenser for 1Kg class Nano satellites.
- Satellite is kept inside a rectangular structure and locked by a swinging door.
- Redundant heating element for wire fusing mechanism to initiate the separation and helical spring to jettison the satellite.
- Micro Switches to monitor the door opening and reed switch to confirm satellite ejection.
- No mass attached with satellite after separation
- Satellite size: 100 mm x 100 mm x 113.5 mm
- Relative velocity : 1 m/s
- Satellite giuded inside the system to reduce the tip off rates
- Operating temperature & Vacuum: 0 c to +600C, < 10-5 torr
-
Power Supply
Current : 402 Amp Voltage : 2.4 V Separation time : 5 sec
Flight Heritage: Successfully deployed STUDSAT in PSLV C15 and SWAYM in PSLV C34
PAYLOAD SEPARATION MECHANISMS
INLS 2U
- Non-pyro dispenser for 2kg class Nano satellites.
- Satellite is kept inside a rectangular structure and locked by a swinging door.
- Redundant heating element for wire fusing mechanism to initiate the separation and helical spring to jettison the satellite.
- Micro Switches to monitor the door opening and reed switch to confirm satellite ejection.
- No mass attached with satellite after separation
- Satellite size: 100 mm x 100 mm x 227.5 mm
- Relative velocity :1.5-1.9 m/s
- Satellite guided inside the system to reduce the tip off rate.
- Operating temperature & Vacuum : 0°c to +65°C, <10-5 torr
-
Power Supply
Current : 402 Amp Voltage : 2.4 V Separation time : 5 sec
Flight Heritage: Successfully deployed SATYABHAMASAT in PSLV C34
PAYLOAD SEPARATION MECHANISMS
INLS 3U
- Non-pyro dispenser for 3kg class Nano satellites.
- Satellite is kept inside a rectangular structure and locked by a swinging door.
- Redundant heating element for wire fusing mechanism to initiate the separation and helical spring to jettison the satellite.
- Micro Switches to monitor the door opening and reed switch to confirm satellite ejection.
- No mass attached with satellite after separation
- Satellite size: 100 mm x 100 mm x 340 mm
- Relative velocity : 1.5 m/s
- Satellite guided inside the system to reduce the tip off rate
- Operating temperature & Vacuum : 0°c to +65°C, < 10-5 torr
-
Power Supply
Current : 402 Amp Voltage : 2.4 V Separation time : 5 sec
System set to launch a customer satellite in PSLV C43
PAYLOAD SEPARATION MECHANISMS
IWL 150
- ISRO Wedge Lock Separation system for 10Kg class satellites.
- Solenoid based pin puller release.
- System is having device level redundancy.
- Fully resettable, Low shock, non-pyro technic, non-consumable and debris-free separation system
- Mounting I/F = 150mm
- System mass:2 kg
- System size: 224 mm x 209 mm x 91 mm
- Relative velocity : 1-1.5 m/s
- Inbuilt guiding feature to reduce the tip off rates.
- Operating temperature E Vacuum :
-15°c to +70°C, < 10-5torr -
Power Supply
Current : Current: 8-10 Amp Voltage : 22-28V Separation time : <25ms from command
Flight heritage: Successfully deployed PISAT in PSLV C35, INS - 1A, and INS-1B in PSLV C37
Payload Separation Mechanisms
IBL230
- ISRO Ball Lock Separation system for 35Kg class satellites.
- Pyro thruster based release.
- System is having device level redundancy.
- Compact and debris-free release system.
- Mounting I/F = 230mm
- System mass:2.5 kg
- System size: 170 mm x 280 mm x 60 mm
- Relative velocity : 1 m/s
- Inbuilt guiding feature to reduce the tip off rates.
- Operating temperature & Vacuum-15°c to +70°C, < 10-5 torr
-
Power Supply
Current : 5A Time : 10ms
Flight heritage: Successfully deployed small satellites like Moon
Impact Probe(MIP), ALSAT-1B, PROITERES, SRMSAT, VESSELSAT-1 etc. in PSLV flights.
PAYLOAD SEPARATION MECHANISMS
IBL 298
- ISRO Ball Lock Separation system for 150Kg class satellites.
- Pyro thruster based release.
- System is having device level redundancy.
- Compact and debris-free release system.
- Mounting I/F = 298mm
- System mass:4.5 kg
- System size:258mm x 351 mm x 91mm
- Relative velocity : 1-1.2 m/s
- Inbuilt guiding feature to reduce the tip off rates.
- Operating temperature & Vacuum :
-15°c to +70°C, < 10-5 torr -
Power Supply
Current : 5A Time : 10ms
Flight heritage: Successfully deployed over 60 small satellites from USA, France, Germany, Canada, Indonesia, Singapore, Algeria and other countries.
Payload Separation Mechanisms
937IF Clamp Band
- ISRO Clamp band system with 937mm dia interface suitable up to 2300 Kg satellites.
- Release by redundant bolt cutters.
- System preload can be varied to cater to different satellite inertial properties.
- Joint Category : Good
- Inbuilt tuning features for spring thrusters to cater to varying relative velocity requirements.
- Operating temperature a Vacuum : -15°c to +60°C, <10-5torr
-
Power Supply
Current : 5A Time : 10ms
Flight heritage: Successfully flown in 40 PSLV missions and 08 GSLV missions.
PAYLOAD SEPARATION MECHANISMS
1194IF CLAMP BAND
- ISRO Clamp band system with 1194mm dia interface suitable up to 4000 Kg satellites.
- Release by redundant bolt cutter actuation.
- System preload can be varied to cater to different satellite inertial properties.
- Tension Release device employed to reduce the separation shock.
- Joint Category : Good
- Inbuilt tuning features for spring thrusters to cater to varying relative velocity requirements.
- Operating temperature B Vacuum : -15°c to +60°C, <10-5torr
-
Power Supply
Current : 5A Time : 10ms
Flight heritage: Successfully employed in the GSLV Mk-III X mission for the separation of Crew Module.