11D428
| 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 (vac.) | 129.16 N (29.04 lbf) |
| Chamber pressure | 0.88 MPa (128 psi) |
| Isp (vac.) | 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).
Versions
This engine has been used with certain variations in manned Russian space program since the Salyut 6 in Soviet times. The three main versions are:[4]
- 11D428: Delivered in 1970 for use in Salyut 1.
- 11D428M: Version developed for the Yantar-2K platform. It reached space on the first launch, Kosmos 697 on August 6, 1974.
- 11D428A (AKA RDMT-135): Version developed for the Soyuz 7K-S, it flew on Kosmos 670, Kosmos 772 and Kosmos 869. Later used on the KTDU-426.[5]
- 11D428A-10: Thruster used on the Zvezda ISS Module. Originally developed for the Mir Core Module.
- 11D428A-14: Thruster used on the Zvezda ISS module.
- 11D428A-16 (AKA RDMT-135M): Improved specific impulse version. Used on the KTDU-80 since Soyuz TM-28.[6]
- 11D428AF-16:Thruster version developed for the Fobos-Grunt planetary sample mission.
| 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 kN (29,300 lbf) | 129.16 kN (29,040 lbf) | 123.5 kN (27,800 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] | ||
See also
References
- 1 2 "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). pp. 75–81. Retrieved 2015-07-25.
- ↑ Pillet, Nicolas. "Le système de propulsion du vaisseau Soyouz" [The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com. Retrieved 2015-07-14.
- 1 2 "Двухкомпонентный ракетный двигатель малой тяги 11Д428А-16" [Bipropellant thruster 11D428A-16] (in Russian). NIIMash. Retrieved 2015-07-30.
- ↑ "История" [History] (in Russian). NIIMash. Retrieved 2015-07-30.
- ↑ "RDMT-135". Encyclopedia Astronautica. Retrieved 2015-07-30.
- ↑ RKK Energia (June 1999). "3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System)". Soyuz Crew Operations Manual (SoyCOM) (ROP-19) Final. NASASpaceFlight.com. pp. 122–129. (subscription required (help)).
- ↑ "Двухкомпонентный ракетный двигатель малой тяги 11Д428АФ-16" [Bipropellant thruster 11D428AF-16] (in Russian). NIIMash. Retrieved 2015-07-30.
- ↑ "Серийный двухкомпонентный ракетный двигатель малой тяги 11Д428А" [Bipropellant thruster 11D428A] (PDF) (in Russian). NIIMash. Retrieved 2015-07-25.
- ↑ "RDMT-100". Encyclopedia Astronautica. Retrieved 2015-07-30.
External links
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