| S1.5400A1 | |
| Country Of Origin: | USSR |
| First Date: | 1960-10-10 |
| Last Date: | 2010-09-30 |
| Designer: | OKB-1 V. M. Melnikov |
| Purpose: | Upper Stage |
| Associated: | Molniya |
| Predecessor: | S1.5400 |
| Successor: | RD-58 |
| Status: | Retired |
| Type: | liquid |
| Fuel: | kerosene T-1 |
| Oxidiser: | LOX |
| Cycle: | Staged combustion |
| Combustion Chamber: | 1 |
| Thrust(Vac): | 66.69kN |
| Chamber Pressure: | 5.4MPa |
| Specific Impulse Vacuum: | 340 seconds |
| Burn Time: | up to 207 s |
| Dry Weight: | 153kg (337lb) |
| Used In: | Molniya Blok-L |
The S1.5400 (GRAU Index 11D33) was a Soviet single-nozzle liquid-propellant rocket engine burning liquid oxygen and kerosene in an oxidizer-rich staged combustion cycle, being the first rocket engine to use this cycle in the world. It was designed by V. M. Melnikov, an alumnus of Isaev, within Korolev's Bureau, for the Molniya fourth stage, the Block-L. It was also the first Soviet engine designed for start and restart in vacuum and had the highest Isp at the time of its deployment.
Its development took from 1958 to 1960. The first production run was started in May 1960, and it passed all the firing tests. Its first flight failed before the Block-L was activated. The first success was in a Venera flight during 1961. 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 63.74kN to 66.69kN and Isp from 338.5 s to 340 s, while keeping the same mass.
The engine used titanium alloy in its main combustion chamber to tolerate temperatures of up to 700C. The turbopump initial spin-up is pyrotechnic. The engine is attached to a Cardan suspension, which enables it to gimbal up to 3° in two axes.