11D428

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11D428A-16
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[edit]

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]

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[edit]

References[edit]

  1. ^ a b "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. 
  2. ^ Pillet, Nicolas. "Le système de propulsion du vaisseau Soyouz" [The propulsion system of the Soyuz spacecraft] (in French). Kosmonavtika.com. Retrieved 2015-07-14. 
  3. ^ a b "Двухкомпонентный ракетный двигатель малой тяги 11Д428А-16" [Bipropellant thruster 11D428A-16] (in Russian). NIIMash. Retrieved 2015-07-30. 
  4. ^ "История" [History] (in Russian). NIIMash. Retrieved 2015-07-30. 
  5. ^ "RDMT-135". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-07-30. 
  6. ^ 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)). 
  7. ^ "Двухкомпонентный ракетный двигатель малой тяги 11Д428АФ-16" [Bipropellant thruster 11D428AF-16] (in Russian). NIIMash. Retrieved 2015-07-30. 
  8. ^ "Серийный двухкомпонентный ракетный двигатель малой тяги 11Д428А" [Bipropellant thruster 11D428A] (PDF) (in Russian). NIIMash. Retrieved 2015-07-25. 
  9. ^ "RDMT-100". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-07-30. 

External links[edit]