| 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) |
| Chamberpressure | 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 sinceSoyuz TM-28 andProgress sinceProgress M-36 | |
| References | |
| References | [1][2][3] |
The11D428A-16 (manufacturer's nameRDMT-135M) is aliquidpressure-fedrocket engine burningN2O4/UDMH with anO/F of 1.85. It is used for crew-ratedspacecraft propulsion applications. It is currently used in theKTDU-80 spacecraft propulsion module. The previous version, the11D428A (manufacturer's nameRDMT-135) is still used as thereaction control system thrusters of theZvezdaISS 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 aspecific 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 thecrewedRussian space program since theSalyut 6 inSoviet times. The three main versions are:[4]
| Engine | 11D428A | 11D428A-16 | 11D428AF-16 |
|---|---|---|---|
| Development | 1968–1974 | 1968–1977 | 1993–1997 |
| Engine Type | Liquidpressure-fedrocket 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 andSoyuz-TM | Soyuz-TMA,Salyut-6,Salyut-7,Mir Core Module,Zvezda | Fobos-Grunt |
| References | [1][3][7][8][9] | ||
Spacecraft engines and motors | ||
|---|---|---|
| Liquid fuel engines |  | |
| Solid propellant motors | ||
| Related articles | ||