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Its development took from 1958 to 1960.[3] The first production run was started on May 1960, and it passed all the firing tests.[9] Its first flight failed before the Block-L was activated and it was in a Venera flight during 1961 that it had its first success. Between 1961 and 1964 it went through an improvement program that ended up in the S1.5400A1 version (GRAU Index 11D33M). It improved thrust from 63.74 kilonewtons (14,330 lbf) to 66.69 kilonewtons (14,990 lbf) and isp from 338.5s to 340s, while keeping weight the same.[6][7]
The engine used titanium alloy in its main combustion chamber to tolerate temperatures of up to 700 °C (1,292 °F). The turbopump initial spin-up is pyrotechnic. The engine is attached to a Cardan suspension which enables it to gimbal up to 3 degrees in two axes.[5][9]
^ abcdSutton, George Paul (November 2005). "Section 4.2 Engine Systems". History of Liquid Propellant Rocket Engines. AIAA. p. 66. ISBN978-1563476495.|access-date= requires |url= (help)
^ abcEckardt, Dietrich (2014). Gas Turbine Powerhouse. Oldenbourg Wissenschaftsverlag. p. 377. ISBN978-3110359626.|access-date= requires |url= (help)
^ abcdeSutton, George Paul (November 2005). "Section 8.11 Korolev's Design Buerau, late NPO Energiya". History of Liquid Propellant Rocket Engines. AIAA. pp. 721–724. ISBN978-1563476495.|access-date= requires |url= (help)
