• ISRO’s geosynchronous satellite launch vehicle (GSLV) rocket failed to inject the latest earth observation satellite EOS-03 into the orbit due to a failure to ignite the cryogenic stage.

• The launch of GSLV-F10 took place at 5.43 am on August 12 as scheduled. Performance of first and second stages was normal. However, cryogenic upper stage ignition did not happen due to technical anomaly. The mission could not be accomplished as intended, ISRO said.

• It was the eighth flight with indigenous cryogenic engine, 14th flight of the GSLV and also marked the 79th launch vehicle mission from Sriharikota.

• An earth observation satellite — EOS-01 —  was launched in November 2020 by PSLV-C49.

What is cryogenic upper stage?

• The cryogenic upper stage employs the vital technology that enhances the payload capability to make the vehicle suitable for launching communication satellites. 

• ISRO’s Cryogenic Upper Stage Project (CUSP) envisaged the design and development of the indigenous Cryogenic Upper Stage to replace the stage procured from Russia and used in GSLV flights.

• The indigenous cryogenic upper stage was successfully flight-tested onboard GSLV-D5 launch vehicle on January 5, 2014 for the launch of communication satellite GSAT-14.

• Only six countries, including India, have developed this technology, which is challenging considering the special materials, alloys and fabrication processes required. 

• A cryogenic rocket stage is more efficient and provides more thrust for every kilogram of propellant it burns compared to solid and earth-storable liquid propellant rocket stages. 

• Cryogenic stage is technically a very complex system due to its use of propellants at extremely low temperatures and the associated thermal and structural problems. 

• Cryogenic engine makes use of Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) as propellants. Oxygen liquifies at -183°C and Hydrogen at -253°C.

• Specific impulse (a measure of the efficiency) achievable with cryogenic propellants (Liquid Hydrogen and Liquid Oxygen) is much higher compared to earth-storable liquid and solid propellants, giving it a substantial payload advantage. 

GSLV-F10 mission

• The 51.70 metre tall rocket with four stages, the first to carry a four-metre diameter ‘Ogive Payload Fairing’ at the top of the vehicle to accommodate larger payloads.

• The rocket was supposed to place the EOS into the Geosynchronous Transfer Orbit, 19 minutes after lift-off.

The objectives of the mission were:

• To provide near real-time imaging of large area regions at frequent intervals.

• For quick monitoring of natural disasters, episodic events  and any short term events. 

• To obtain spectral signatures for agriculture, forestry, water bodies as well as for disaster warning, cyclone monitoring, cloud burst and thunderstorm monitoring, etc.

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