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Russian rocket engine From Wikipedia, the free encyclopedia
The S5.98M, also known as the 14D30, is a Russian rocket engine, currently powering the Briz upper stages.[2][5] It was designed by KB KhIMMASH, the famous Isaev designed bureau, and it burns UDMH and N2O4 in a gas-generator cycle.[1][3][6][7]
Country of origin | Russia |
---|---|
First flight | 1990-11-20 |
Manufacturer | KB KhIMMASH |
Application | Upper Stage |
Associated LV | Proton-M and Rokot |
Predecessor | S5.92 |
Status | In Production |
Liquid-fuel engine | |
Propellant | N2O4 / UDMH |
Mixture ratio | 2.0 |
Cycle | Gas Generator |
Configuration | |
Chamber | 1 |
Performance | |
Thrust, vacuum | 19.62 kilonewtons (4,410 lbf) |
Chamber pressure | 9.8 megapascals (1,420 psi) |
Specific impulse, vacuum | 328.6 seconds |
Burn time | 3,200 seconds |
Restarts | 7 |
Dimensions | |
Length | 1,150 millimetres (45 in) |
Diameter | 948 millimetres (37.3 in) |
Dry mass | 95 kilograms (209 lb) |
Used in | |
Briz-M and Rokot | |
References | |
References | [1][2][3][4] |
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