| 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] |
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]
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| Liquid fuel |
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| Solid fuel |
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