Global Information11D428 information
| Country of origin | Russia |
|---|---|
| Date | 1993–1997 |
| First flight | 1997-10-05 (Progress M-36) |
| Designer | NIIMash |
| Application | RCS thruster |
| Predecessor | 11D428A |
| Successor | 11D428AF-16 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 1.85±0.15 |
| Cycle | pressure fed |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 129.16 N (29.04 lbf) |
| Chamber pressure | 0.88 MPa (128 psi) |
| Specific impulse, vacuum | 291 s (2.85 km/s) |
| Restarts | 500,000 |
| Dimensions | |
| Dry weight | 1.5 kg (3.3 lb) |
| Used in | |
| Soyuz since Soyuz TM-28 and Progress since Progress M-36 | |
| References | |
| References | [1][2][3] |
The 11D428A-16 (manufacturer's name RDMT-135M) is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the KTDU-80 spacecraft propulsion module. The previous version, the 11D428A (manufacturer's name RDMT-135) is still used as the reaction control system thrusters of the Zvezda ISS module. The 11D428A-16 generates 129.16 N (29.04 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and achieves a specific impulse of 291 s (2.85 km/s). It is rated for 500,000 starts with a certified ignition time of 0.03 seconds to 2000 seconds. Each unit weights 1.5 kg (3.3 lb).
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