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An upgraded version of the engine has a chamber pressure of 58.5 bar as compared to 52.5 bar in the older version and produces a thrust of 800 kN. The engine is capable of gimballing. For launches from 2018 a 6% increased thrust version of the Vikas engine was developed. It was demonstrated on 29 March 2018 in the GSAT 6A launch second stage ...
The SCE-200 (also referred as Semi-Cryogenic Engine-200) is a 2 MN thrust class liquid rocket engine, being developed to power Indian Space Research Organisation's (ISRO) existing LVM3 and upcoming heavy and super heavy-lift launch vehicles.
The CE-20 is the first Indian cryogenic engine to feature a gas-generator cycle. [10] The engine produces a nominal thrust of 200 kN, but has an operating thrust range between 180 kN to 220 kN and can be set to any fixed values between these limits.
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ISRO's Liquid Propulsion Systems Centre (LPSC) was set up in 1985 and started working on a more powerful engine, Vikas, based upon the French Viking. [26] Two years later, facilities to test liquid-fuelled rocket engines were established and development and testing of various rocket engines thrusters began.
The earliest versions, developed in 1965, had a sea-level thrust of about 190 kN. By 1971, the thrust had improved to 540 kN, with resulting engine named Viking 1 and adopted for the Ariane program. The engine first flown on the Ariane 1 rocket in 1979 was Viking 2, with thrust further improved to 611 kN.
Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [e] Oxidiser: fuel ratio