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SEPARATION SYSTEMS

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

INLS 1U Separation System

Non-pyro release system for 1Kg class nano satellites

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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

INLS 2U Separation System

Non-pyro release system for 2KG class nano satellites

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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

INLS 3U Separation System

Non-pyro release system for 3.5Kg class satellites

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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

IWL150 Separation System

Solenoid release system for 10Kg class satellites

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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

IBL 230 Separation System

Pyro thruster based system for 35Kg class satellites.

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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.

IBL298 Separation System

Pyro thruster based system for 150Kg class satellites

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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.

937IF Separation System

Clamp band based system for 2300Kg class satellites

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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.

1194IF Separation System

Clamp band based system for 4000Kg class satellites

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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.