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).
Country of origin | Russia |
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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] |
This engine has been used with certain variations in the crewed Russian space program since the Salyut 6 in Soviet 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] |