S5.98M
S5.98M|
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| Country of origin |
Russia |
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| First flight |
1990-11-20 |
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| Manufacturer |
KB KhIMMASH |
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| Application |
Upper Stage |
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| Associated L/V |
Proton-M and Rokot |
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| Predecessor |
none |
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| Status |
In Production |
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| Liquid-fuel engine |
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| Propellant |
N2O4 / UDMH |
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| Mixture ratio |
2.0 |
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| Cycle |
Stage Combustion |
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| Configuration |
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| Chamber |
1 |
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| Performance |
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| Thrust (vac.) |
19.62 kilonewtons (4,410 lbf) |
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| Chamber pressure |
9.8 megapascals (1,420 psi) |
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| Isp (vac.) |
328.6 seconds |
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| Burn time |
3,200 seconds |
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| Restarts |
7 |
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| Dimensions |
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| Length |
1,150 millimetres (45 in) |
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| Diameter |
948 millimetres (37.3 in) |
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| Dry weight |
95 kilograms (209 lb) |
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| Used in |
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|
Briz-M and Rokot |
| References |
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| References |
[1][2][3][4] |
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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 closed cycle UDMH and nitrogen tetroxide.[3][1][6]
See also
- Briz-M - The upper stage stage that is powered by the S5.98M.
- Proton-M - The heavy lift rocket that uses the Briz-M stage.
- Rokot - The light lift rocket that uses the smaller Briz-KM stage.
- Khrunichev - The manufacturer of the Briz stage and the corporate parent of the designer bureau.
References
External links
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| | Solid fuel | US | |
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