| 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 mass | 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).
This engine has been used with certain variations in the crewed Russian space program since the Salyut 6inSoviet times. The three main versions are:[4]
| Engine | 11D428A | 11D428A-16 | 11D428AF-16 |
|---|---|---|---|
| Development | 1968–1974 | 1968–1977 | 1993–1997 |
| Engine Type | Liquid pressure-fed rocket engine | ||
| Propellant | N2O4/UDMH with 1.85 O/F ratio | ||
| Thrust | 130.5 N (29.3 lbf) | 129.16 N (29.04 lbf) | 123.5 N (27.8 lbf) |
| isp | 1:56 Exp. Nozzle:290 s (2.8 km/s) 1:150 Exp. Nozzle:302 s (2.96 km/s) |
291 s (2.85 km/s) | 306.2 s (3.003 km/s) |
| Nominal Inlet Pressure | 1.77 MPa (257 psi) | 1.76 MPa (255 psi) | 1.47 MPa (213 psi) |
| Nozzle | 1 | 1 | 1 |
| Burn time | 570s | 2700s | 50,000s |
| Ignitions | 500,000 | ||
| Ignition time | 0.03 to 2000s | ||
| Mass | 1.2 kg (2.6 lb) | 1.5 kg (3.3 lb) | 1.9 kg (4.2 lb) |
| Length | 274 mm (10.8 in) | 289.5 mm (11.40 in) | 372 mm (14.6 in) |
| Diameter | 98 mm (3.9 in) | 157.4 mm (6.20 in) | |
| Uses | Soyuz 7K-S, Soyuz-T and Soyuz-TM | Soyuz-TMA, Salyut-6, Salyut-7, Mir Core Module, Zvezda | Fobos-Grunt |
| References | [1][3][7][8][9] | ||
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Spacecraft engines and motors
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|---|---|---|
| Liquid fuel engines |
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| Solid propellant motors |
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| Related articles |
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