ISRO has crossed yet another major milestone by successfully conducting the
Flight Acceptance Hot Test of Indigenous Cryogenic Engine at Liquid Propulsion
Systems Centres (LPSC) Mahendragiri facilities on December 18, 2008. This
Cryogenic Engine is identified for the first indigenously developed Cryogenic
Stage to be used in the next Geosynchronous Launch Vehicle mission (GSLV -D3).
The indigenous cryogenic engine develops a thrust of 73 kilo Newtons (kN) in
vacuum with a specific impulse of 454 seconds and provides a payload capability
of 2200 Kg to Geosynchronous Transfer Orbit (GTO) for GSLV. The Engine works on
Staged Combustion Cycle with an integrated turbopump running at around 42,000
rotations per minute (rpm). It is also equipped with two steering engines
developing a thrust of 2 kN each to enable three-axis control of the launch
vehicle during the mission. Another unique feature of this engine is the closed
loop control of both thrust and mixture ratio, which ensures optimum propellant
utilisation for the mission.
The hot test was carried out for a planned duration of 200 seconds during which
the engine was operated in the nominal and 13% uprated thrust regimes. All the
propulsion parameters during the test were found satisfactory and closely
matched with predictions.
The Cryogenic Engine will be further integrated with propellant tanks, stage
structures and associated feed lines to realise the first fully integrated
indigenous flight Cryogenic Stage by the middle of 2009.