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ISRO to launch India's newest SSLV Launch Vehicle

SSLV-D1 manifests EOS-02 and "AzaadiSAT" 8 kg CubeSat built by 750 girl students from Government Schools in India.

SSLV-D1/EOS-02 Summary (S.I & HDE)

Chennai, August 05, 2022 The Indian Space Research Organisation (ISRO) to launch its New Launch Vehicle "SSLV" is scheduled to launch from the First Launch Pad at SHAR, Shri Harikota at 09:18 IST (03:48 UTC) on August 07, 2022.

SSLV-D1 is a mission to launch EOS-02 (Earth Observation Satellite-02) and a ride-share satellite AzaadiSAT, into 356 km Low Earth Orbit.

SSLV-D1 Poised at FLP, SHAR (ISRO)

The Small Satellite Launch Vehicle (SSLV) is the new launch vehicle of ISRO capable of launching Mini, Micro or Nanosatellites (10 to 500 kg mass) to 500 km orbit. SSLV is a three-stage vehicle with all solid propulsion stages. The satellite insertion into the intended orbit is achieved through a liquid propulsion-based Velocity Trimming Module (VTM).


Payloads on SSLV-D1 Mission

EOS-02

EOS-02 (ISRO)

EOS-02 is an experimental optical remote sensing satellite with a high spatial resolution. The objective of EOS-02 is to realise and fly an experimental imaging satellite with a short turn-around time and to demonstrate launch-on-demand capability. EOS-02 belongs to microsatellite series of spacecrafts. The bus configuration is derived from IMS-1 (Indian Mini Satellite-1) bus.

Mission Objectives

  • EOS-02 has a Design and development of an agile and experimental satellite with an imaging payload.

  • Providing inputs on thermal anomalies towards supporting applications in the domains of geo-environmental studies, forestry, hydrology, agriculture, soil, coastal studies, etc.

The New technologies realised for the Microsat series of spacecrafts include Payloads with a common fore optics and metallic primary mirror realised with the limited mass and volume of Microsat Bus.


EOS-02 Configuration


EOS-02 (ISRO)
  • The structural construction is of aluminum honeycomb. Cuboid structure of 552 mm x 600 mm x 600 mm is designed and qualified for a total spacecraft mass of 145 kg.

  • Mainframe/Bus subsystems are integrated independent payloads. All payload elements are accommodated on the top deck.

  • The two solar panels generating 350 W power are the only deployable appendages.

  • The platform is highly agile with a maneuverability of 3.5°/s and a pointing accuracy of 0.1".

  • The payload data transmission rate is 32 Mbps in X-Band.